Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Xfoil prediction polar at RE=2,000,000 Ncrit=9
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Airfoil: Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Reynolds number: 2,000,000 Max Cl/Cd: 87.27 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-tip-ns-2000000.txt Download as CSV file: xf-prandtl-d-tip-ns-2000000.csv |
XFOIL Version 6.96
Calculated polar for: Prandtl-D tip - NASA Preliminary Research Aerody
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 2.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.6478 0.22807 0.22709 0.0693 1.0000 0.0033
-17.500 -0.8801 0.15788 0.15653 0.0308 1.0000 0.0022
-17.250 -0.9019 0.14784 0.14642 0.0262 1.0000 0.0021
-17.000 -0.9298 0.13696 0.13545 0.0211 1.0000 0.0021
-16.750 -0.9423 0.12990 0.12836 0.0179 1.0000 0.0020
-16.500 -0.9527 0.12349 0.12192 0.0150 1.0000 0.0020
-16.250 -0.9835 0.11288 0.11121 0.0099 1.0000 0.0020
-16.000 -0.9951 0.10646 0.10476 0.0070 1.0000 0.0020
-15.750 -1.0280 0.09608 0.09429 0.0018 1.0000 0.0020
-15.500 -1.0310 0.09154 0.08973 -0.0003 1.0000 0.0019
-15.250 -1.0685 0.08045 0.07852 -0.0061 1.0000 0.0019
-15.000 -1.0809 0.07401 0.07202 -0.0096 1.0000 0.0019
-14.750 -1.1032 0.06552 0.06341 -0.0147 1.0000 0.0019
-14.500 -1.1292 0.05625 0.05398 -0.0210 1.0000 0.0019
-14.250 -1.1345 0.05098 0.04862 -0.0248 1.0000 0.0019
-14.000 -1.1331 0.04709 0.04466 -0.0277 1.0000 0.0019
-13.750 -1.1681 0.03828 0.03556 -0.0336 1.0000 0.0019
-13.500 -1.1656 0.03571 0.03291 -0.0346 1.0000 0.0019
-13.250 -1.1749 0.03237 0.02940 -0.0348 1.0000 0.0019
-13.000 -1.1978 0.02866 0.02544 -0.0323 1.0000 0.0019
-12.750 -1.1864 0.02795 0.02470 -0.0308 1.0000 0.0019
-12.500 -1.1975 0.02596 0.02252 -0.0263 1.0000 0.0019
-12.250 -1.2053 0.02389 0.02025 -0.0218 1.0000 0.0019
-12.000 -1.2056 0.02189 0.01802 -0.0183 1.0000 0.0020
-11.750 -1.1918 0.02096 0.01700 -0.0165 1.0000 0.0019
-11.500 -1.1876 0.01907 0.01487 -0.0133 1.0000 0.0020
-11.250 -1.1741 0.01797 0.01363 -0.0113 1.0000 0.0021
-11.000 -1.1610 0.01676 0.01227 -0.0091 1.0000 0.0023
-10.750 -1.1433 0.01598 0.01141 -0.0075 1.0000 0.0024
-10.500 -1.1233 0.01544 0.01082 -0.0063 1.0000 0.0026
-10.250 -1.1035 0.01486 0.01018 -0.0051 1.0000 0.0028
-10.000 -1.0821 0.01444 0.00972 -0.0040 1.0000 0.0030
-9.750 -1.0618 0.01388 0.00910 -0.0027 1.0000 0.0031
-9.500 -1.0405 0.01343 0.00861 -0.0016 1.0000 0.0032
-9.250 -1.0188 0.01303 0.00817 -0.0005 1.0000 0.0034
-9.000 -0.9972 0.01264 0.00773 0.0006 1.0000 0.0035
-8.750 -0.9756 0.01223 0.00728 0.0018 1.0000 0.0036
-8.500 -0.9538 0.01187 0.00688 0.0029 1.0000 0.0036
-8.250 -0.9317 0.01155 0.00654 0.0040 1.0000 0.0037
-8.000 -0.9122 0.01096 0.00582 0.0056 1.0000 0.0040
-7.750 -0.8917 0.01050 0.00530 0.0071 1.0000 0.0048
-7.500 -0.8707 0.01014 0.00494 0.0085 1.0000 0.0056
-7.250 -0.8492 0.00986 0.00465 0.0098 1.0000 0.0067
-7.000 -0.8293 0.00945 0.00427 0.0114 1.0000 0.0106
-6.750 -0.8042 0.00922 0.00403 0.0119 0.9997 0.0121
-6.500 -0.7720 0.00888 0.00373 0.0108 0.9987 0.0169
-6.250 -0.7393 0.00862 0.00349 0.0096 0.9973 0.0209
-6.000 -0.7064 0.00831 0.00322 0.0084 0.9958 0.0282
-5.750 -0.6730 0.00802 0.00298 0.0070 0.9943 0.0375
-5.500 -0.6422 0.00775 0.00275 0.0063 0.9918 0.0477
-5.250 -0.6106 0.00745 0.00254 0.0054 0.9890 0.0620
-5.000 -0.5778 0.00719 0.00234 0.0042 0.9866 0.0759
-4.750 -0.5443 0.00689 0.00214 0.0029 0.9845 0.0969
-4.500 -0.5143 0.00660 0.00195 0.0023 0.9795 0.1211
-4.250 -0.4805 0.00635 0.00178 0.0010 0.9750 0.1414
-4.000 -0.4469 0.00610 0.00163 -0.0004 0.9684 0.1655
-3.750 -0.4129 0.00588 0.00149 -0.0017 0.9590 0.1887
-3.500 -0.3830 0.00571 0.00136 -0.0022 0.9450 0.2107
-3.250 -0.3559 0.00557 0.00125 -0.0019 0.9284 0.2311
-3.000 -0.3299 0.00544 0.00115 -0.0014 0.9084 0.2549
-2.750 -0.3047 0.00533 0.00105 -0.0008 0.8853 0.2797
-2.500 -0.2798 0.00525 0.00097 0.0000 0.8598 0.3027
-2.250 -0.2548 0.00518 0.00089 0.0007 0.8333 0.3275
-2.000 -0.2295 0.00513 0.00082 0.0013 0.8065 0.3503
-1.750 -0.2042 0.00509 0.00077 0.0019 0.7782 0.3735
-1.250 -0.1537 0.00495 0.00067 0.0031 0.7250 0.4364
-1.000 -0.1281 0.00491 0.00063 0.0037 0.6982 0.4651
-0.750 -0.1024 0.00488 0.00061 0.0042 0.6702 0.4916
-0.500 -0.0766 0.00486 0.00059 0.0047 0.6428 0.5186
-0.250 -0.0507 0.00484 0.00057 0.0052 0.6174 0.5467
0.000 -0.0249 0.00483 0.00057 0.0056 0.5891 0.5747
0.250 0.0007 0.00483 0.00057 0.0062 0.5592 0.6045
0.500 0.0265 0.00482 0.00057 0.0067 0.5346 0.6331
0.750 0.0524 0.00484 0.00059 0.0071 0.5077 0.6592
1.000 0.0779 0.00485 0.00061 0.0077 0.4802 0.6895
1.250 0.1032 0.00486 0.00063 0.0083 0.4533 0.7195
1.500 0.1285 0.00489 0.00067 0.0089 0.4265 0.7476
1.750 0.1535 0.00493 0.00071 0.0096 0.3976 0.7772
2.000 0.1780 0.00500 0.00076 0.0103 0.3657 0.8075
2.250 0.2027 0.00502 0.00082 0.0111 0.3437 0.8387
2.500 0.2273 0.00505 0.00089 0.0119 0.3222 0.8690
2.750 0.2525 0.00510 0.00096 0.0126 0.2980 0.8988
3.000 0.2804 0.00519 0.00105 0.0127 0.2731 0.9270
3.250 0.3168 0.00534 0.00117 0.0108 0.2467 0.9492
3.500 0.3600 0.00556 0.00130 0.0072 0.2179 0.9594
3.750 0.4024 0.00578 0.00144 0.0039 0.1936 0.9653
4.000 0.4350 0.00603 0.00158 0.0028 0.1681 0.9737
4.250 0.4670 0.00629 0.00175 0.0019 0.1440 0.9795
4.500 0.4960 0.00652 0.00190 0.0016 0.1268 0.9853
4.750 0.5302 0.00675 0.00207 0.0002 0.1087 0.9877
5.000 0.5625 0.00708 0.00228 -0.0009 0.0827 0.9903
5.250 0.5940 0.00739 0.00249 -0.0018 0.0647 0.9930
5.500 0.6260 0.00766 0.00270 -0.0028 0.0507 0.9947
5.750 0.6600 0.00794 0.00291 -0.0043 0.0383 0.9960
6.000 0.6935 0.00823 0.00314 -0.0057 0.0290 0.9974
6.250 0.7269 0.00848 0.00336 -0.0070 0.0234 0.9986
6.500 0.7597 0.00876 0.00363 -0.0082 0.0176 0.9996
6.750 0.7872 0.00902 0.00387 -0.0082 0.0147 1.0000
7.000 0.8095 0.00932 0.00415 -0.0072 0.0107 1.0000
7.250 0.8324 0.00957 0.00440 -0.0062 0.0091 1.0000
7.500 0.8543 0.00997 0.00478 -0.0050 0.0059 1.0000
7.750 0.8769 0.01030 0.00512 -0.0040 0.0050 1.0000
8.000 0.8991 0.01068 0.00551 -0.0029 0.0043 1.0000
8.250 0.9204 0.01120 0.00611 -0.0016 0.0037 1.0000
8.500 0.9409 0.01182 0.00686 -0.0002 0.0034 1.0000
8.750 0.9628 0.01224 0.00733 0.0009 0.0033 1.0000
9.000 0.9852 0.01259 0.00770 0.0018 0.0033 1.0000
9.250 1.0070 0.01300 0.00816 0.0029 0.0032 1.0000
9.500 1.0285 0.01344 0.00864 0.0040 0.0031 1.0000
9.750 1.0497 0.01391 0.00916 0.0051 0.0031 1.0000
10.000 1.0703 0.01444 0.00976 0.0063 0.0030 1.0000
10.250 1.0903 0.01503 0.01042 0.0076 0.0029 1.0000
10.500 1.1115 0.01546 0.01088 0.0086 0.0027 1.0000
10.750 1.1315 0.01601 0.01150 0.0099 0.0026 1.0000
11.000 1.1506 0.01663 0.01219 0.0112 0.0025 1.0000
11.250 1.1711 0.01708 0.01265 0.0123 0.0023 1.0000
11.500 1.1890 0.01778 0.01342 0.0137 0.0022 1.0000
11.750 1.2055 0.01861 0.01432 0.0153 0.0020 1.0000
12.000 1.2173 0.01986 0.01571 0.0174 0.0019 1.0000
12.250 1.2069 0.02300 0.01925 0.0222 0.0017 1.0000
12.500 1.2293 0.02311 0.01935 0.0229 0.0018 1.0000
12.750 1.2172 0.02588 0.02241 0.0275 0.0017 1.0000
13.000 1.2049 0.02790 0.02461 0.0321 0.0017 1.0000
13.250 1.2238 0.02809 0.02479 0.0330 0.0017 1.0000
13.500 1.2012 0.03159 0.02854 0.0358 0.0017 1.0000
13.750 1.1708 0.03710 0.03433 0.0354 0.0017 1.0000
14.000 1.1541 0.04254 0.03996 0.0324 0.0017 1.0000
14.250 1.1502 0.04689 0.04442 0.0294 0.0017 1.0000
14.500 1.1603 0.04921 0.04676 0.0278 0.0017 1.0000
14.750 1.1323 0.05855 0.05629 0.0210 0.0017 1.0000
15.000 1.1030 0.06844 0.06634 0.0146 0.0017 1.0000
15.250 1.0958 0.07402 0.07197 0.0115 0.0017 1.0000
15.500 1.1078 0.07594 0.07388 0.0106 0.0018 1.0000
15.750 1.0315 0.09441 0.09258 0.0005 0.0017 1.0000
16.000 1.0164 0.10138 0.09961 -0.0029 0.0017 1.0000
16.250 1.0232 0.10411 0.10233 -0.0040 0.0018 1.0000
16.500 1.0026 0.11234 0.11062 -0.0081 0.0018 1.0000
16.750 0.9696 0.12359 0.12195 -0.0137 0.0018 1.0000
17.000 0.9730 0.12704 0.12541 -0.0152 0.0019 1.0000
17.250 0.9145 0.14508 0.14360 -0.0241 0.0018 1.0000
17.500 0.9182 0.14856 0.14710 -0.0257 0.0020 1.0000
17.750 0.8781 0.16385 0.16249 -0.0330 0.0019 1.0000
18.750 0.5945 0.19989 0.19884 -0.0457 0.0037 1.0000
19.000 0.5994 0.20310 0.20206 -0.0476 0.0036 1.0000
19.250 0.5991 0.20880 0.20775 -0.0500 0.0034 1.0000
19.500 0.6041 0.21238 0.21134 -0.0520 0.0034 1.0000
19.750 0.6094 0.21576 0.21472 -0.0539 0.0034 1.0000
20.000 0.6144 0.21929 0.21826 -0.0558 0.0033 1.0000
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