SA7035 (sa7035-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 50,000 Max Cl/Cd: 37.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7035-il-50000-n5.txt Download as CSV file: xf-sa7035-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4146 0.11566 0.10857 -0.0202 1.0000 0.0921
-9.500 -0.4127 0.11212 0.10509 -0.0219 1.0000 0.0904
-9.250 -0.4166 0.10426 0.09722 -0.0280 1.0000 0.0455
-9.000 -0.4098 0.10057 0.09357 -0.0278 1.0000 0.0439
-8.750 -0.4068 0.09701 0.09007 -0.0288 1.0000 0.0426
-8.500 -0.4058 0.09328 0.08641 -0.0301 1.0000 0.0413
-8.250 -0.4066 0.08948 0.08270 -0.0317 1.0000 0.0401
-8.000 -0.4099 0.08556 0.07889 -0.0334 1.0000 0.0390
-7.750 -0.4164 0.08156 0.07501 -0.0354 1.0000 0.0379
-7.250 -0.4327 0.06993 0.06336 -0.0447 1.0000 0.0346
-7.000 -0.4333 0.06643 0.05987 -0.0449 1.0000 0.0343
-6.750 -0.4342 0.06270 0.05609 -0.0451 1.0000 0.0340
-6.500 -0.4336 0.05898 0.05227 -0.0451 1.0000 0.0338
-6.250 -0.4310 0.05527 0.04839 -0.0451 1.0000 0.0337
-6.000 -0.4262 0.05146 0.04432 -0.0449 1.0000 0.0339
-5.750 -0.4183 0.04785 0.04037 -0.0446 1.0000 0.0341
-5.500 -0.4072 0.04438 0.03642 -0.0441 1.0000 0.0346
-5.250 -0.3952 0.04112 0.03293 -0.0435 1.0000 0.0358
-5.000 -0.3803 0.03861 0.03020 -0.0428 1.0000 0.0372
-4.750 -0.3629 0.03599 0.02721 -0.0420 1.0000 0.0381
-4.500 -0.3433 0.03345 0.02424 -0.0412 1.0000 0.0388
-4.250 -0.3224 0.03116 0.02150 -0.0403 1.0000 0.0400
-4.000 -0.3005 0.02919 0.01914 -0.0392 1.0000 0.0416
-3.750 -0.2781 0.02757 0.01713 -0.0381 1.0000 0.0452
-3.500 -0.2572 0.02620 0.01567 -0.0371 1.0000 0.0506
-3.250 -0.2352 0.02497 0.01420 -0.0359 1.0000 0.0572
-3.000 -0.2131 0.02385 0.01301 -0.0350 1.0000 0.0689
-2.750 -0.1903 0.02274 0.01187 -0.0343 1.0000 0.0897
-2.500 -0.1640 0.02129 0.01082 -0.0348 0.9990 0.1653
-2.250 -0.1296 0.01952 0.01039 -0.0371 0.9921 0.4193
-2.000 -0.1031 0.01871 0.01052 -0.0358 0.9837 0.6684
-1.750 -0.0581 0.01818 0.01033 -0.0368 0.9763 0.9446
-1.500 -0.0108 0.01832 0.00991 -0.0414 0.9661 1.0000
-1.250 0.0315 0.01856 0.00971 -0.0447 0.9560 1.0000
-1.000 0.0707 0.01876 0.00955 -0.0474 0.9445 1.0000
-0.750 0.1085 0.01894 0.00941 -0.0498 0.9324 1.0000
-0.500 0.1463 0.01910 0.00932 -0.0520 0.9202 1.0000
-0.250 0.1843 0.01925 0.00926 -0.0542 0.9081 1.0000
0.000 0.2229 0.01938 0.00919 -0.0563 0.8961 1.0000
0.250 0.2603 0.01947 0.00914 -0.0581 0.8840 1.0000
0.500 0.2960 0.01954 0.00908 -0.0595 0.8713 1.0000
0.750 0.3299 0.01959 0.00902 -0.0605 0.8578 1.0000
1.000 0.3616 0.01963 0.00899 -0.0610 0.8433 1.0000
1.250 0.3919 0.01968 0.00898 -0.0611 0.8279 1.0000
1.500 0.4215 0.01972 0.00899 -0.0611 0.8122 1.0000
1.750 0.4510 0.01975 0.00898 -0.0610 0.7961 1.0000
2.000 0.4806 0.01977 0.00898 -0.0609 0.7798 1.0000
2.250 0.5102 0.01978 0.00897 -0.0606 0.7632 1.0000
2.500 0.5398 0.01978 0.00897 -0.0603 0.7466 1.0000
2.750 0.5668 0.01986 0.00904 -0.0597 0.7278 1.0000
3.000 0.5940 0.01994 0.00912 -0.0590 0.7086 1.0000
3.250 0.6222 0.01999 0.00916 -0.0584 0.6900 1.0000
3.500 0.6477 0.02017 0.00939 -0.0575 0.6689 1.0000
3.750 0.6744 0.02031 0.00953 -0.0567 0.6485 1.0000
4.000 0.6996 0.02054 0.00978 -0.0558 0.6267 1.0000
4.250 0.7256 0.02075 0.01003 -0.0549 0.6054 1.0000
4.500 0.7498 0.02106 0.01037 -0.0540 0.5822 1.0000
4.750 0.7747 0.02135 0.01067 -0.0530 0.5597 1.0000
5.000 0.7985 0.02171 0.01106 -0.0520 0.5359 1.0000
5.250 0.8219 0.02212 0.01155 -0.0510 0.5117 1.0000
5.500 0.8455 0.02254 0.01199 -0.0499 0.4883 1.0000
5.750 0.8684 0.02302 0.01251 -0.0489 0.4644 1.0000
6.000 0.8906 0.02356 0.01311 -0.0478 0.4399 1.0000
6.250 0.9126 0.02413 0.01372 -0.0467 0.4157 1.0000
6.500 0.9343 0.02473 0.01438 -0.0456 0.3920 1.0000
6.750 0.9547 0.02541 0.01516 -0.0444 0.3669 1.0000
7.000 0.9748 0.02613 0.01596 -0.0432 0.3425 1.0000
7.250 0.9943 0.02691 0.01678 -0.0419 0.3187 1.0000
7.500 1.0130 0.02776 0.01769 -0.0406 0.2952 1.0000
7.750 1.0307 0.02869 0.01872 -0.0393 0.2712 1.0000
8.000 1.0471 0.02968 0.01981 -0.0378 0.2478 1.0000
8.250 1.0624 0.03076 0.02092 -0.0363 0.2250 1.0000
8.500 1.0761 0.03194 0.02221 -0.0347 0.2017 1.0000
8.750 1.0885 0.03324 0.02352 -0.0330 0.1808 1.0000
9.000 1.1000 0.03468 0.02507 -0.0313 0.1605 1.0000
9.250 1.1091 0.03623 0.02661 -0.0295 0.1429 1.0000
9.500 1.1184 0.03800 0.02846 -0.0277 0.1268 1.0000
9.750 1.1255 0.03987 0.03050 -0.0258 0.1122 1.0000
10.000 1.1298 0.04178 0.03246 -0.0237 0.1007 1.0000
10.250 1.1348 0.04389 0.03464 -0.0218 0.0909 1.0000
10.500 1.1382 0.04619 0.03717 -0.0200 0.0816 1.0000
10.750 1.1409 0.04865 0.03972 -0.0185 0.0745 1.0000
11.000 1.1429 0.05127 0.04254 -0.0171 0.0682 1.0000
11.250 1.1431 0.05412 0.04552 -0.0160 0.0631 1.0000
11.500 1.1409 0.05732 0.04902 -0.0151 0.0584 1.0000
11.750 1.1408 0.06036 0.05213 -0.0145 0.0551 1.0000
12.000 1.1376 0.06415 0.05612 -0.0142 0.0524 1.0000
12.250 1.1279 0.06870 0.06104 -0.0147 0.0505 1.0000
12.500 1.1156 0.07368 0.06632 -0.0160 0.0487 1.0000
12.750 1.1025 0.07906 0.07194 -0.0178 0.0475 1.0000
13.000 1.0876 0.08508 0.07817 -0.0205 0.0466 1.0000
13.250 1.0685 0.09238 0.08570 -0.0243 0.0467 1.0000
13.500 1.0424 0.10192 0.09549 -0.0299 0.0482 1.0000
13.750 1.0140 0.11293 0.10666 -0.0366 0.0500 1.0000
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Polar data table (+)
Polar graphs
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