S7075 (9%) (s7075-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 200,000 Max Cl/Cd: 74.02 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7075-il-200000-n5.txt Download as CSV file: xf-s7075-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7075 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3360 0.08093 0.07768 -0.0349 1.0000 0.0200
-8.500 -0.3411 0.07852 0.07530 -0.0333 1.0000 0.0196
-8.250 -0.4134 0.08428 0.08087 -0.0349 1.0000 0.0197
-8.000 -0.4247 0.08238 0.07903 -0.0327 1.0000 0.0193
-7.750 -0.4294 0.07923 0.07592 -0.0336 0.9980 0.0188
-7.500 -0.4187 0.07357 0.07027 -0.0409 0.9921 0.0181
-7.250 -0.4092 0.05259 0.04899 -0.0660 0.9819 0.0153
-7.000 -0.3965 0.04589 0.04202 -0.0716 0.9757 0.0151
-6.750 -0.3766 0.03874 0.03439 -0.0775 0.9716 0.0149
-6.500 -0.3580 0.03335 0.02845 -0.0801 0.9667 0.0149
-6.250 -0.3353 0.02904 0.02352 -0.0818 0.9622 0.0149
-6.000 -0.3068 0.02577 0.01964 -0.0834 0.9594 0.0152
-5.750 -0.2762 0.02341 0.01691 -0.0852 0.9575 0.0158
-5.500 -0.2470 0.02242 0.01579 -0.0862 0.9547 0.0169
-5.250 -0.2218 0.02112 0.01423 -0.0860 0.9502 0.0175
-5.000 -0.1911 0.01963 0.01246 -0.0868 0.9473 0.0179
-4.750 -0.1584 0.01832 0.01093 -0.0879 0.9451 0.0183
-4.500 -0.1249 0.01719 0.00965 -0.0891 0.9432 0.0189
-4.250 -0.0967 0.01635 0.00868 -0.0892 0.9394 0.0196
-4.000 -0.0695 0.01566 0.00789 -0.0891 0.9347 0.0204
-3.750 -0.0384 0.01487 0.00706 -0.0899 0.9314 0.0218
-3.500 -0.0050 0.01432 0.00647 -0.0910 0.9289 0.0245
-3.250 0.0226 0.01387 0.00596 -0.0910 0.9241 0.0292
-3.000 0.0506 0.01339 0.00546 -0.0909 0.9191 0.0375
-2.750 0.0823 0.01286 0.00501 -0.0917 0.9155 0.0619
-2.500 0.1122 0.01229 0.00472 -0.0923 0.9114 0.1249
-2.250 0.1371 0.01176 0.00455 -0.0920 0.9047 0.2180
-2.000 0.1674 0.01128 0.00434 -0.0925 0.9003 0.3035
-1.750 0.1932 0.01081 0.00423 -0.0922 0.8941 0.4121
-1.500 0.2191 0.01034 0.00413 -0.0918 0.8879 0.5247
-1.250 0.2455 0.00988 0.00406 -0.0911 0.8828 0.6396
-1.000 0.2658 0.00964 0.00412 -0.0888 0.8744 0.7431
-0.750 0.2912 0.00947 0.00403 -0.0876 0.8682 0.8085
-0.500 0.3145 0.00938 0.00395 -0.0862 0.8591 0.8480
-0.250 0.3397 0.00924 0.00382 -0.0850 0.8507 0.8812
0.000 0.3689 0.00907 0.00365 -0.0847 0.8422 0.9141
0.250 0.4069 0.00893 0.00350 -0.0865 0.8319 0.9550
0.500 0.4444 0.00883 0.00334 -0.0884 0.8210 1.0000
0.750 0.4717 0.00880 0.00324 -0.0881 0.8083 1.0000
1.000 0.4988 0.00879 0.00315 -0.0877 0.7936 1.0000
1.250 0.5261 0.00879 0.00307 -0.0874 0.7767 1.0000
1.500 0.5537 0.00879 0.00299 -0.0871 0.7578 1.0000
1.750 0.5812 0.00883 0.00293 -0.0868 0.7364 1.0000
2.000 0.6084 0.00892 0.00288 -0.0864 0.7127 1.0000
2.250 0.6347 0.00905 0.00289 -0.0859 0.6865 1.0000
2.500 0.6606 0.00923 0.00294 -0.0853 0.6599 1.0000
2.750 0.6860 0.00945 0.00302 -0.0847 0.6330 1.0000
3.000 0.7109 0.00969 0.00314 -0.0840 0.6053 1.0000
3.250 0.7353 0.00996 0.00327 -0.0832 0.5766 1.0000
3.500 0.7594 0.01026 0.00346 -0.0825 0.5466 1.0000
3.750 0.7831 0.01058 0.00364 -0.0816 0.5157 1.0000
4.000 0.8064 0.01093 0.00385 -0.0808 0.4844 1.0000
4.250 0.8295 0.01129 0.00409 -0.0799 0.4532 1.0000
4.500 0.8523 0.01169 0.00437 -0.0790 0.4212 1.0000
4.750 0.8748 0.01211 0.00466 -0.0781 0.3876 1.0000
5.000 0.8969 0.01257 0.00497 -0.0772 0.3529 1.0000
5.250 0.9188 0.01305 0.00531 -0.0762 0.3196 1.0000
5.500 0.9408 0.01355 0.00570 -0.0753 0.2873 1.0000
5.750 0.9625 0.01408 0.00610 -0.0744 0.2551 1.0000
6.000 0.9837 0.01466 0.00653 -0.0734 0.2222 1.0000
6.750 1.0466 0.01652 0.00804 -0.0706 0.1385 1.0000
7.000 1.0673 0.01716 0.00860 -0.0696 0.1178 1.0000
7.250 1.0876 0.01783 0.00920 -0.0686 0.0986 1.0000
7.500 1.1075 0.01853 0.00985 -0.0675 0.0832 1.0000
7.750 1.1274 0.01921 0.01053 -0.0664 0.0715 1.0000
8.000 1.1469 0.01991 0.01124 -0.0652 0.0629 1.0000
8.250 1.1650 0.02070 0.01204 -0.0638 0.0560 1.0000
8.500 1.1837 0.02142 0.01282 -0.0625 0.0507 1.0000
8.750 1.1994 0.02235 0.01377 -0.0609 0.0460 1.0000
9.000 1.2169 0.02309 0.01462 -0.0594 0.0432 1.0000
9.250 1.2323 0.02390 0.01554 -0.0577 0.0408 1.0000
9.500 1.2459 0.02479 0.01650 -0.0557 0.0388 1.0000
9.750 1.2572 0.02584 0.01761 -0.0534 0.0372 1.0000
10.000 1.2659 0.02713 0.01896 -0.0510 0.0357 1.0000
10.250 1.2789 0.02812 0.02009 -0.0491 0.0347 1.0000
10.500 1.2910 0.02920 0.02132 -0.0472 0.0336 1.0000
10.750 1.3025 0.03032 0.02258 -0.0453 0.0323 1.0000
11.000 1.3132 0.03153 0.02390 -0.0435 0.0311 1.0000
11.250 1.3230 0.03284 0.02533 -0.0417 0.0303 1.0000
11.500 1.3318 0.03426 0.02686 -0.0399 0.0295 1.0000
11.750 1.3396 0.03582 0.02852 -0.0381 0.0288 1.0000
12.000 1.3462 0.03761 0.03042 -0.0364 0.0281 1.0000
12.250 1.3518 0.03980 0.03271 -0.0348 0.0274 1.0000
12.500 1.3585 0.04159 0.03471 -0.0333 0.0268 1.0000
12.750 1.3640 0.04343 0.03677 -0.0319 0.0261 1.0000
13.000 1.3679 0.04541 0.03896 -0.0307 0.0252 1.0000
13.250 1.3707 0.04746 0.04119 -0.0296 0.0242 1.0000
13.500 1.3724 0.04968 0.04357 -0.0288 0.0233 1.0000
13.750 1.3734 0.05196 0.04597 -0.0284 0.0224 1.0000
14.000 1.3729 0.05455 0.04868 -0.0282 0.0216 1.0000
14.250 1.3702 0.05763 0.05187 -0.0282 0.0210 1.0000
14.750 1.3595 0.06516 0.05976 -0.0293 0.0198 1.0000
15.000 1.3532 0.06938 0.06422 -0.0305 0.0193 1.0000
15.250 1.3454 0.07405 0.06912 -0.0322 0.0187 1.0000
15.500 1.3366 0.07916 0.07444 -0.0344 0.0181 1.0000
15.750 1.3263 0.08477 0.08025 -0.0371 0.0177 1.0000
16.000 1.3136 0.09109 0.08677 -0.0403 0.0174 1.0000
16.250 1.3003 0.09785 0.09371 -0.0440 0.0171 1.0000
16.500 1.2849 0.10535 0.10140 -0.0483 0.0169 1.0000
16.750 1.2659 0.11395 0.11019 -0.0534 0.0168 1.0000
17.000 1.2410 0.12437 0.12083 -0.0598 0.0170 1.0000
17.250 1.2035 0.13868 0.13540 -0.0688 0.0176 1.0000
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Polar data table (+)
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