SA7038 (sa7038-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 200,000 Max Cl/Cd: 72.63 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7038-il-200000-n5.txt Download as CSV file: xf-sa7038-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3709 0.08186 0.07854 -0.0363 1.0000 0.0198
-7.750 -0.3787 0.07992 0.07666 -0.0342 1.0000 0.0190
-7.500 -0.3949 0.07817 0.07499 -0.0316 1.0000 0.0188
-7.250 -0.3939 0.07415 0.07102 -0.0348 0.9967 0.0180
-7.000 -0.3749 0.06655 0.06338 -0.0462 0.9889 0.0171
-6.750 -0.3505 0.05736 0.05407 -0.0595 0.9823 0.0166
-6.500 -0.3279 0.04993 0.04644 -0.0681 0.9748 0.0169
-6.250 -0.2996 0.04231 0.03845 -0.0759 0.9704 0.0173
-6.000 -0.2801 0.03365 0.02910 -0.0802 0.9621 0.0160
-5.750 -0.2511 0.02718 0.02166 -0.0831 0.9578 0.0150
-5.500 -0.2245 0.02455 0.01855 -0.0838 0.9522 0.0148
-5.250 -0.1957 0.02235 0.01595 -0.0845 0.9472 0.0148
-5.000 -0.1640 0.02038 0.01361 -0.0857 0.9437 0.0149
-4.750 -0.1372 0.01884 0.01183 -0.0857 0.9375 0.0151
-4.500 -0.1078 0.01754 0.01033 -0.0860 0.9322 0.0156
-4.250 -0.0762 0.01645 0.00911 -0.0868 0.9281 0.0160
-4.000 -0.0509 0.01565 0.00821 -0.0862 0.9201 0.0167
-3.750 -0.0206 0.01490 0.00738 -0.0866 0.9151 0.0177
-3.500 0.0056 0.01441 0.00680 -0.0861 0.9072 0.0197
-3.250 0.0347 0.01378 0.00608 -0.0862 0.9012 0.0207
-3.000 0.0609 0.01318 0.00539 -0.0858 0.8928 0.0221
-2.750 0.0901 0.01271 0.00484 -0.0858 0.8862 0.0243
-2.500 0.1166 0.01236 0.00440 -0.0853 0.8764 0.0287
-2.250 0.1441 0.01183 0.00397 -0.0850 0.8678 0.0584
-2.000 0.1711 0.01125 0.00369 -0.0849 0.8588 0.1399
-1.750 0.1966 0.01060 0.00354 -0.0848 0.8482 0.2734
-1.500 0.2217 0.00994 0.00343 -0.0844 0.8379 0.4366
-1.250 0.2466 0.00947 0.00334 -0.0836 0.8275 0.5613
-1.000 0.2706 0.00911 0.00327 -0.0824 0.8160 0.6661
-0.750 0.2929 0.00882 0.00321 -0.0805 0.8032 0.7628
-0.500 0.3160 0.00859 0.00312 -0.0787 0.7898 0.8554
-0.250 0.3544 0.00843 0.00293 -0.0802 0.7757 0.9534
0.000 0.3911 0.00840 0.00276 -0.0819 0.7603 1.0000
0.250 0.4174 0.00847 0.00266 -0.0814 0.7445 1.0000
0.500 0.4436 0.00854 0.00260 -0.0809 0.7275 1.0000
0.750 0.4699 0.00864 0.00256 -0.0804 0.7100 1.0000
1.000 0.4961 0.00875 0.00253 -0.0799 0.6918 1.0000
1.250 0.5222 0.00888 0.00252 -0.0795 0.6732 1.0000
1.500 0.5483 0.00903 0.00254 -0.0790 0.6536 1.0000
1.750 0.5742 0.00919 0.00257 -0.0785 0.6341 1.0000
2.000 0.6001 0.00936 0.00264 -0.0780 0.6147 1.0000
2.250 0.6259 0.00954 0.00271 -0.0776 0.5949 1.0000
2.500 0.6516 0.00975 0.00280 -0.0771 0.5753 1.0000
2.750 0.6772 0.00995 0.00291 -0.0766 0.5557 1.0000
3.000 0.7027 0.01017 0.00305 -0.0761 0.5355 1.0000
3.250 0.7280 0.01041 0.00319 -0.0756 0.5153 1.0000
3.500 0.7533 0.01065 0.00335 -0.0751 0.4945 1.0000
3.750 0.7782 0.01092 0.00353 -0.0746 0.4742 1.0000
4.000 0.8033 0.01118 0.00375 -0.0741 0.4534 1.0000
4.250 0.8281 0.01147 0.00396 -0.0736 0.4335 1.0000
4.500 0.8529 0.01176 0.00419 -0.0730 0.4136 1.0000
4.750 0.8774 0.01208 0.00444 -0.0725 0.3935 1.0000
5.000 0.9016 0.01242 0.00474 -0.0719 0.3729 1.0000
5.250 0.9257 0.01276 0.00504 -0.0713 0.3518 1.0000
5.500 0.9495 0.01314 0.00535 -0.0707 0.3318 1.0000
5.750 0.9734 0.01351 0.00569 -0.0701 0.3123 1.0000
6.000 0.9969 0.01391 0.00607 -0.0695 0.2934 1.0000
6.250 1.0200 0.01433 0.00646 -0.0688 0.2754 1.0000
6.500 1.0434 0.01475 0.00687 -0.0682 0.2579 1.0000
6.750 1.0662 0.01520 0.00730 -0.0675 0.2400 1.0000
7.000 1.0885 0.01569 0.00777 -0.0667 0.2224 1.0000
7.250 1.1103 0.01621 0.00828 -0.0659 0.2041 1.0000
7.500 1.1319 0.01675 0.00880 -0.0651 0.1857 1.0000
7.750 1.1531 0.01732 0.00936 -0.0642 0.1691 1.0000
8.000 1.1737 0.01792 0.00994 -0.0633 0.1534 1.0000
8.500 1.2135 0.01921 0.01125 -0.0613 0.1241 1.0000
8.750 1.2326 0.01989 0.01195 -0.0601 0.1106 1.0000
9.000 1.2509 0.02062 0.01269 -0.0589 0.0982 1.0000
9.250 1.2682 0.02141 0.01349 -0.0576 0.0856 1.0000
9.500 1.2844 0.02226 0.01433 -0.0562 0.0729 1.0000
9.750 1.2993 0.02317 0.01524 -0.0546 0.0612 1.0000
10.000 1.3126 0.02408 0.01616 -0.0528 0.0513 1.0000
10.250 1.3246 0.02501 0.01716 -0.0508 0.0431 1.0000
10.500 1.3351 0.02603 0.01822 -0.0487 0.0364 1.0000
10.750 1.3433 0.02725 0.01943 -0.0465 0.0301 1.0000
11.000 1.3534 0.02832 0.02063 -0.0445 0.0253 1.0000
11.250 1.3598 0.02970 0.02206 -0.0424 0.0209 1.0000
11.500 1.3650 0.03123 0.02365 -0.0404 0.0160 1.0000
11.750 1.3696 0.03284 0.02539 -0.0384 0.0135 1.0000
12.000 1.3718 0.03473 0.02738 -0.0365 0.0114 1.0000
12.250 1.3713 0.03692 0.02968 -0.0347 0.0103 1.0000
12.500 1.3721 0.03913 0.03208 -0.0333 0.0095 1.0000
12.750 1.3708 0.04165 0.03478 -0.0322 0.0088 1.0000
13.000 1.3688 0.04441 0.03773 -0.0315 0.0083 1.0000
13.250 1.3657 0.04743 0.04092 -0.0311 0.0080 1.0000
13.500 1.3603 0.05093 0.04457 -0.0311 0.0076 1.0000
13.750 1.3524 0.05497 0.04878 -0.0316 0.0074 1.0000
14.000 1.3434 0.05940 0.05338 -0.0326 0.0072 1.0000
14.250 1.3339 0.06416 0.05832 -0.0340 0.0071 1.0000
14.500 1.3227 0.06947 0.06379 -0.0359 0.0070 1.0000
14.750 1.3123 0.07492 0.06942 -0.0381 0.0069 1.0000
15.000 1.3012 0.08071 0.07539 -0.0406 0.0069 1.0000
15.250 1.2892 0.08692 0.08178 -0.0435 0.0068 1.0000
15.500 1.2769 0.09340 0.08843 -0.0466 0.0067 1.0000
15.750 1.2646 0.10007 0.09526 -0.0500 0.0067 1.0000
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Polar data table (+)
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