Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-tip-ns) Reynolds number: 500,000 Max Cl/Cd: 62.73 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-tip-ns-500000.txt Download as CSV file: xf-prandtl-d-tip-ns-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.6332 0.22724 0.22526 0.0632 1.0000 0.0113
-19.750 -0.6290 0.22394 0.22195 0.0611 1.0000 0.0114
-19.500 -0.6245 0.22076 0.21877 0.0590 1.0000 0.0115
-19.250 -0.6198 0.21730 0.21530 0.0571 1.0000 0.0116
-19.000 -0.6149 0.21384 0.21183 0.0552 1.0000 0.0116
-18.750 -0.6100 0.21040 0.20838 0.0533 1.0000 0.0116
-18.500 -0.6053 0.20684 0.20482 0.0514 1.0000 0.0116
-18.250 -0.6044 0.20089 0.19888 0.0495 1.0000 0.0122
-18.000 -0.5977 0.19794 0.19592 0.0482 1.0000 0.0124
-17.750 -0.5911 0.19516 0.19310 0.0468 1.0000 0.0127
-17.500 -0.5853 0.19226 0.19020 0.0453 1.0000 0.0130
-17.250 -0.5797 0.18936 0.18730 0.0437 1.0000 0.0134
-17.000 -0.5746 0.18633 0.18425 0.0419 1.0000 0.0137
-16.750 -0.5695 0.18330 0.18122 0.0402 1.0000 0.0142
-16.500 -0.5649 0.18019 0.17810 0.0385 1.0000 0.0148
-16.250 -0.5605 0.17699 0.17490 0.0366 1.0000 0.0154
-16.000 -0.5567 0.17366 0.17156 0.0347 1.0000 0.0163
-15.750 -0.5536 0.17015 0.16806 0.0326 1.0000 0.0172
-15.500 -0.5519 0.16667 0.16457 0.0298 1.0000 0.0186
-15.250 -0.5485 0.16334 0.16124 0.0278 1.0000 0.0188
-15.000 -0.5458 0.15979 0.15768 0.0258 1.0000 0.0189
-14.750 -0.5437 0.15611 0.15400 0.0238 1.0000 0.0189
-14.500 -0.5659 0.14504 0.14295 0.0200 1.0000 0.0122
-14.250 -0.5636 0.14168 0.13957 0.0182 1.0000 0.0118
-14.000 -0.5708 0.13780 0.13567 0.0161 1.0000 0.0111
-13.500 -0.8439 0.09165 0.08917 -0.0044 1.0000 0.0074
-13.250 -0.8686 0.08128 0.07865 -0.0109 1.0000 0.0072
-13.000 -0.8932 0.07163 0.06887 -0.0175 1.0000 0.0073
-12.750 -0.8900 0.06772 0.06487 -0.0204 1.0000 0.0070
-12.500 -0.9114 0.05960 0.05657 -0.0265 1.0000 0.0070
-12.250 -0.9305 0.05286 0.04964 -0.0312 1.0000 0.0070
-12.000 -0.9490 0.04735 0.04393 -0.0343 1.0000 0.0071
-11.750 -0.9453 0.04531 0.04181 -0.0349 1.0000 0.0069
-11.500 -0.9713 0.04045 0.03668 -0.0347 1.0000 0.0070
-11.250 -0.9797 0.03797 0.03402 -0.0328 1.0000 0.0070
-11.000 -0.9966 0.03491 0.03071 -0.0291 1.0000 0.0071
-10.750 -1.0049 0.03237 0.02794 -0.0253 1.0000 0.0071
-10.500 -1.0074 0.02967 0.02497 -0.0222 1.0000 0.0074
-10.250 -1.0026 0.02750 0.02260 -0.0197 1.0000 0.0076
-10.000 -0.9917 0.02602 0.02098 -0.0177 1.0000 0.0080
-9.750 -0.9796 0.02447 0.01925 -0.0158 1.0000 0.0082
-9.500 -0.9650 0.02321 0.01786 -0.0140 1.0000 0.0086
-9.250 -0.9493 0.02202 0.01653 -0.0123 1.0000 0.0089
-9.000 -0.9331 0.02084 0.01522 -0.0106 1.0000 0.0094
-8.750 -0.9166 0.01970 0.01393 -0.0088 1.0000 0.0099
-8.500 -0.8984 0.01880 0.01292 -0.0073 1.0000 0.0105
-8.250 -0.8773 0.01830 0.01232 -0.0062 1.0000 0.0113
-8.000 -0.8618 0.01705 0.01092 -0.0041 1.0000 0.0121
-7.750 -0.8495 0.01549 0.00922 -0.0014 1.0000 0.0144
-7.500 -0.8297 0.01483 0.00851 0.0001 1.0000 0.0169
-7.250 -0.8086 0.01434 0.00794 0.0014 1.0000 0.0195
-7.000 -0.7913 0.01339 0.00695 0.0034 1.0000 0.0254
-6.750 -0.7693 0.01304 0.00654 0.0045 1.0000 0.0291
-6.500 -0.7501 0.01237 0.00589 0.0061 1.0000 0.0382
-6.250 -0.7298 0.01186 0.00543 0.0075 1.0000 0.0496
-6.000 -0.7092 0.01140 0.00498 0.0089 1.0000 0.0643
-5.750 -0.6890 0.01094 0.00460 0.0103 1.0000 0.0818
-5.500 -0.6685 0.01054 0.00428 0.0117 1.0000 0.1023
-5.250 -0.6480 0.01016 0.00400 0.0131 1.0000 0.1246
-5.000 -0.6272 0.00985 0.00375 0.0144 1.0000 0.1458
-4.750 -0.6067 0.00954 0.00353 0.0158 1.0000 0.1702
-4.500 -0.5862 0.00925 0.00334 0.0172 1.0000 0.1948
-4.250 -0.5657 0.00899 0.00317 0.0185 1.0000 0.2206
-4.000 -0.5453 0.00875 0.00300 0.0199 1.0000 0.2473
-3.750 -0.5211 0.00853 0.00288 0.0204 0.9994 0.2754
-3.500 -0.4828 0.00827 0.00275 0.0180 0.9956 0.3132
-3.250 -0.4455 0.00799 0.00262 0.0158 0.9913 0.3535
-3.000 -0.4079 0.00771 0.00250 0.0136 0.9867 0.3950
-2.750 -0.3701 0.00745 0.00237 0.0113 0.9822 0.4359
-2.500 -0.3340 0.00719 0.00225 0.0095 0.9763 0.4765
-2.250 -0.2947 0.00690 0.00214 0.0071 0.9724 0.5236
-2.000 -0.2610 0.00665 0.00202 0.0059 0.9643 0.5642
-1.750 -0.2230 0.00642 0.00192 0.0038 0.9587 0.6018
-1.500 -0.1909 0.00621 0.00183 0.0031 0.9480 0.6375
-1.250 -0.1589 0.00602 0.00176 0.0025 0.9351 0.6718
-1.000 -0.1287 0.00585 0.00168 0.0023 0.9196 0.7065
-0.500 -0.0748 0.00560 0.00158 0.0034 0.8799 0.7699
-0.250 -0.0492 0.00552 0.00156 0.0044 0.8563 0.8022
0.000 -0.0237 0.00549 0.00154 0.0053 0.8312 0.8333
0.250 0.0026 0.00549 0.00154 0.0061 0.8041 0.8623
0.500 0.0307 0.00553 0.00156 0.0064 0.7746 0.8882
0.750 0.0622 0.00562 0.00159 0.0060 0.7439 0.9109
1.000 0.0974 0.00576 0.00164 0.0047 0.7128 0.9290
1.250 0.1351 0.00594 0.00171 0.0028 0.6775 0.9424
1.500 0.1739 0.00614 0.00180 0.0006 0.6422 0.9519
1.750 0.2091 0.00636 0.00189 -0.0008 0.6073 0.9611
2.000 0.2468 0.00661 0.00200 -0.0028 0.5693 0.9669
2.250 0.2812 0.00686 0.00212 -0.0042 0.5298 0.9747
2.500 0.3187 0.00713 0.00224 -0.0062 0.4854 0.9806
2.750 0.3553 0.00741 0.00235 -0.0082 0.4421 0.9864
3.000 0.3936 0.00766 0.00246 -0.0105 0.4025 0.9912
3.250 0.4316 0.00793 0.00259 -0.0129 0.3608 0.9956
3.500 0.4706 0.00818 0.00269 -0.0155 0.3200 0.9994
3.750 0.4954 0.00838 0.00278 -0.0151 0.2889 1.0000
4.000 0.5170 0.00859 0.00289 -0.0139 0.2597 1.0000
4.250 0.5387 0.00881 0.00303 -0.0128 0.2334 1.0000
4.500 0.5604 0.00908 0.00319 -0.0117 0.2060 1.0000
4.750 0.5822 0.00936 0.00340 -0.0106 0.1809 1.0000
5.000 0.6040 0.00967 0.00362 -0.0095 0.1559 1.0000
5.250 0.6260 0.00999 0.00386 -0.0084 0.1324 1.0000
5.500 0.6480 0.01033 0.00413 -0.0073 0.1117 1.0000
5.750 0.6695 0.01075 0.00444 -0.0062 0.0896 1.0000
6.000 0.6913 0.01116 0.00479 -0.0051 0.0702 1.0000
6.250 0.7125 0.01167 0.00521 -0.0039 0.0538 1.0000
6.500 0.7337 0.01219 0.00572 -0.0027 0.0412 1.0000
6.750 0.7555 0.01264 0.00618 -0.0015 0.0333 1.0000
7.000 0.7759 0.01328 0.00683 -0.0002 0.0264 1.0000
7.250 0.7978 0.01372 0.00730 0.0009 0.0222 1.0000
7.500 0.8154 0.01476 0.00842 0.0028 0.0174 1.0000
7.750 0.8366 0.01531 0.00904 0.0040 0.0148 1.0000
8.000 0.8562 0.01604 0.00984 0.0055 0.0130 1.0000
8.250 0.8670 0.01793 0.01191 0.0083 0.0111 1.0000
8.500 0.8821 0.01933 0.01348 0.0104 0.0106 1.0000
8.750 0.9011 0.02015 0.01440 0.0118 0.0101 1.0000
9.000 0.9205 0.02084 0.01522 0.0131 0.0095 1.0000
9.250 0.9372 0.02190 0.01641 0.0147 0.0089 1.0000
9.500 0.9520 0.02323 0.01790 0.0166 0.0085 1.0000
9.750 0.9655 0.02468 0.01951 0.0186 0.0083 1.0000
10.000 0.9772 0.02628 0.02130 0.0206 0.0081 1.0000
10.250 0.9866 0.02806 0.02328 0.0228 0.0079 1.0000
10.500 0.9972 0.02936 0.02471 0.0248 0.0075 1.0000
10.750 1.0027 0.03120 0.02674 0.0271 0.0074 1.0000
11.000 1.0035 0.03328 0.02902 0.0298 0.0073 1.0000
11.250 1.0008 0.03480 0.03064 0.0330 0.0070 1.0000
11.500 0.9910 0.03725 0.03330 0.0360 0.0069 1.0000
11.750 0.9803 0.04009 0.03632 0.0374 0.0068 1.0000
12.000 0.9677 0.04374 0.04016 0.0373 0.0068 1.0000
12.250 0.9373 0.05062 0.04730 0.0340 0.0065 1.0000
12.500 0.9408 0.05361 0.05043 0.0319 0.0069 1.0000
12.750 0.9228 0.06064 0.05764 0.0267 0.0068 1.0000
13.000 0.9015 0.06922 0.06641 0.0202 0.0069 1.0000
17.500 0.5571 0.18787 0.18573 -0.0352 0.0131 1.0000
17.750 0.5620 0.19087 0.18873 -0.0369 0.0127 1.0000
18.000 0.5674 0.19373 0.19159 -0.0385 0.0123 1.0000
18.250 0.5729 0.19659 0.19446 -0.0400 0.0120 1.0000
18.500 0.5788 0.19936 0.19725 -0.0415 0.0117 1.0000
18.750 0.5853 0.20213 0.20004 -0.0428 0.0115 1.0000
19.000 0.5916 0.20529 0.20322 -0.0440 0.0112 1.0000
19.250 0.5929 0.21093 0.20883 -0.0460 0.0108 1.0000
19.500 0.5976 0.21436 0.21227 -0.0478 0.0108 1.0000
19.750 0.6025 0.21769 0.21561 -0.0496 0.0108 1.0000
20.000 0.6073 0.22106 0.21899 -0.0514 0.0108 1.0000
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