S8038 (13%) (s8038-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 100,000 Max Cl/Cd: 43.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8038-il-100000-n5.txt Download as CSV file: xf-s8038-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6220 0.09702 0.09146 -0.0327 1.0000 0.0267
-12.500 -0.6752 0.08100 0.07529 -0.0436 1.0000 0.0258
-12.250 -0.7140 0.07130 0.06537 -0.0502 1.0000 0.0253
-12.000 -0.7453 0.06442 0.05824 -0.0538 1.0000 0.0249
-11.750 -0.7675 0.05958 0.05318 -0.0551 1.0000 0.0250
-11.500 -0.7861 0.05564 0.04902 -0.0551 1.0000 0.0249
-11.250 -0.8017 0.05236 0.04551 -0.0540 1.0000 0.0249
-11.000 -0.8141 0.04963 0.04258 -0.0518 1.0000 0.0250
-10.750 -0.8245 0.04726 0.04000 -0.0487 1.0000 0.0251
-10.500 -0.8317 0.04509 0.03763 -0.0453 1.0000 0.0253
-10.250 -0.8328 0.04290 0.03521 -0.0425 1.0000 0.0256
-10.000 -0.8303 0.04079 0.03288 -0.0399 1.0000 0.0259
-9.750 -0.8246 0.03877 0.03063 -0.0374 1.0000 0.0263
-9.500 -0.8160 0.03686 0.02848 -0.0351 1.0000 0.0268
-9.250 -0.8051 0.03507 0.02647 -0.0330 1.0000 0.0274
-9.000 -0.7925 0.03345 0.02464 -0.0310 1.0000 0.0282
-8.750 -0.7795 0.03200 0.02302 -0.0290 1.0000 0.0293
-8.500 -0.7667 0.03075 0.02179 -0.0270 1.0000 0.0305
-8.250 -0.7530 0.02961 0.02059 -0.0251 1.0000 0.0318
-8.000 -0.7389 0.02845 0.01935 -0.0230 1.0000 0.0331
-7.750 -0.7250 0.02731 0.01811 -0.0208 1.0000 0.0343
-7.500 -0.7115 0.02628 0.01697 -0.0185 1.0000 0.0356
-7.250 -0.7008 0.02519 0.01589 -0.0160 1.0000 0.0371
-7.000 -0.6888 0.02429 0.01497 -0.0135 1.0000 0.0393
-6.750 -0.6762 0.02349 0.01411 -0.0111 1.0000 0.0423
-6.500 -0.6647 0.02264 0.01326 -0.0086 1.0000 0.0464
-6.250 -0.6522 0.02190 0.01247 -0.0061 1.0000 0.0527
-6.000 -0.6409 0.02107 0.01169 -0.0035 1.0000 0.0606
-5.750 -0.6291 0.02034 0.01101 -0.0010 1.0000 0.0734
-5.500 -0.6011 0.01941 0.01030 -0.0020 0.9947 0.1057
-5.250 -0.5697 0.01841 0.00968 -0.0037 0.9865 0.1648
-5.000 -0.5396 0.01751 0.00914 -0.0051 0.9776 0.2364
-4.750 -0.5092 0.01674 0.00870 -0.0063 0.9686 0.3063
-4.500 -0.4790 0.01608 0.00836 -0.0072 0.9593 0.3798
-4.250 -0.4502 0.01560 0.00814 -0.0076 0.9491 0.4462
-4.000 -0.4177 0.01531 0.00802 -0.0084 0.9408 0.5040
-3.750 -0.3852 0.01514 0.00792 -0.0090 0.9316 0.5500
-3.500 -0.3528 0.01502 0.00780 -0.0096 0.9224 0.5859
-3.250 -0.3164 0.01493 0.00767 -0.0110 0.9148 0.6152
-3.000 -0.2848 0.01486 0.00754 -0.0114 0.9043 0.6403
-2.750 -0.2485 0.01479 0.00743 -0.0126 0.8965 0.6618
-2.500 -0.2169 0.01472 0.00731 -0.0130 0.8856 0.6802
-2.250 -0.1842 0.01466 0.00719 -0.0136 0.8753 0.6971
-2.000 -0.1485 0.01459 0.00705 -0.0147 0.8666 0.7131
-1.750 -0.1183 0.01455 0.00697 -0.0148 0.8546 0.7277
-1.500 -0.0866 0.01450 0.00687 -0.0152 0.8436 0.7413
-1.250 -0.0533 0.01444 0.00674 -0.0159 0.8334 0.7544
-1.000 -0.0240 0.01440 0.00665 -0.0159 0.8211 0.7675
-0.750 0.0060 0.01438 0.00661 -0.0159 0.8088 0.7790
-0.500 0.0366 0.01436 0.00655 -0.0161 0.7971 0.7900
-0.250 0.0674 0.01434 0.00646 -0.0163 0.7859 0.8014
0.000 0.0959 0.01434 0.00643 -0.0161 0.7733 0.8127
0.250 0.1255 0.01435 0.00644 -0.0161 0.7608 0.8229
0.500 0.1545 0.01436 0.00642 -0.0161 0.7485 0.8339
0.750 0.1838 0.01438 0.00639 -0.0160 0.7364 0.8451
1.000 0.2155 0.01440 0.00640 -0.0164 0.7239 0.8545
1.250 0.2444 0.01443 0.00642 -0.0164 0.7099 0.8652
1.500 0.2742 0.01447 0.00645 -0.0166 0.6957 0.8760
1.750 0.3065 0.01453 0.00650 -0.0172 0.6812 0.8853
2.000 0.3374 0.01459 0.00654 -0.0176 0.6662 0.8960
2.250 0.3702 0.01465 0.00659 -0.0184 0.6498 0.9062
2.500 0.4044 0.01472 0.00663 -0.0194 0.6315 0.9154
2.750 0.4369 0.01479 0.00666 -0.0202 0.6124 0.9262
3.000 0.4724 0.01488 0.00675 -0.0217 0.5909 0.9351
3.250 0.5075 0.01499 0.00683 -0.0230 0.5693 0.9447
3.500 0.5416 0.01511 0.00692 -0.0243 0.5465 0.9550
3.750 0.5781 0.01525 0.00701 -0.0261 0.5210 0.9638
4.000 0.6122 0.01541 0.00714 -0.0276 0.4929 0.9747
4.250 0.6462 0.01561 0.00726 -0.0290 0.4622 0.9860
4.500 0.6808 0.01587 0.00741 -0.0308 0.4270 0.9971
5.000 0.7111 0.01645 0.00773 -0.0266 0.3659 1.0000
5.250 0.7238 0.01683 0.00797 -0.0240 0.3356 1.0000
5.500 0.7373 0.01727 0.00827 -0.0216 0.3063 1.0000
5.750 0.7511 0.01776 0.00862 -0.0192 0.2786 1.0000
6.000 0.7653 0.01829 0.00902 -0.0169 0.2541 1.0000
6.250 0.7798 0.01884 0.00946 -0.0147 0.2321 1.0000
6.500 0.7942 0.01943 0.00996 -0.0125 0.2130 1.0000
6.750 0.8091 0.02003 0.01047 -0.0104 0.1967 1.0000
7.000 0.8244 0.02063 0.01103 -0.0084 0.1833 1.0000
7.250 0.8402 0.02124 0.01162 -0.0065 0.1713 1.0000
7.500 0.8558 0.02188 0.01225 -0.0046 0.1608 1.0000
7.750 0.8704 0.02259 0.01289 -0.0026 0.1519 1.0000
8.000 0.8867 0.02323 0.01359 -0.0009 0.1434 1.0000
8.250 0.9014 0.02399 0.01431 0.0010 0.1369 1.0000
8.500 0.9177 0.02469 0.01509 0.0027 0.1301 1.0000
8.750 0.9315 0.02551 0.01585 0.0046 0.1246 1.0000
9.000 0.9479 0.02625 0.01670 0.0062 0.1187 1.0000
9.250 0.9627 0.02704 0.01753 0.0080 0.1139 1.0000
9.500 0.9766 0.02797 0.01841 0.0097 0.1098 1.0000
9.750 0.9916 0.02879 0.01940 0.0114 0.1052 1.0000
10.000 1.0042 0.02964 0.02030 0.0134 0.1010 1.0000
10.250 1.0159 0.03061 0.02124 0.0153 0.0976 1.0000
10.500 1.0295 0.03161 0.02239 0.0170 0.0940 1.0000
10.750 1.0414 0.03261 0.02353 0.0188 0.0903 1.0000
11.000 1.0519 0.03362 0.02458 0.0206 0.0871 1.0000
11.250 1.0633 0.03481 0.02576 0.0221 0.0844 1.0000
11.500 1.0736 0.03609 0.02727 0.0237 0.0816 1.0000
11.750 1.0821 0.03740 0.02875 0.0254 0.0785 1.0000
12.000 1.0899 0.03871 0.03016 0.0269 0.0760 1.0000
12.250 1.0977 0.04007 0.03157 0.0283 0.0738 1.0000
12.500 1.1072 0.04166 0.03317 0.0294 0.0719 1.0000
12.750 1.1102 0.04360 0.03541 0.0308 0.0701 1.0000
13.000 1.1119 0.04566 0.03771 0.0320 0.0681 1.0000
13.250 1.1129 0.04777 0.04001 0.0329 0.0662 1.0000
13.500 1.1136 0.04993 0.04230 0.0336 0.0646 1.0000
13.750 1.1150 0.05206 0.04451 0.0341 0.0631 1.0000
14.000 1.1185 0.05414 0.04662 0.0345 0.0617 1.0000
14.250 1.1168 0.05700 0.04960 0.0347 0.0606 1.0000
14.500 1.1049 0.06091 0.05380 0.0342 0.0598 1.0000
14.750 1.0894 0.06546 0.05863 0.0332 0.0590 1.0000
15.000 1.0706 0.07072 0.06415 0.0314 0.0584 1.0000
15.250 1.0464 0.07708 0.07076 0.0285 0.0578 1.0000
15.500 1.0145 0.08520 0.07914 0.0242 0.0577 1.0000
15.750 0.9606 0.09836 0.09256 0.0161 0.0579 1.0000
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Polar data table (+)
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