GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 416A AIRFOIL (goe416a-il) Reynolds number: 100,000 Max Cl/Cd: 47.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe416a-il-100000-n5.txt Download as CSV file: xf-goe416a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 416A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4623 0.09431 0.08970 -0.0210 1.0000 0.0274
-10.500 -0.4696 0.08828 0.08369 -0.0233 1.0000 0.0266
-10.250 -0.4819 0.08125 0.07667 -0.0265 1.0000 0.0260
-10.000 -0.4996 0.07391 0.06930 -0.0303 1.0000 0.0256
-9.750 -0.5197 0.06703 0.06243 -0.0341 1.0000 0.0254
-9.500 -0.5407 0.06085 0.05617 -0.0376 1.0000 0.0253
-9.250 -0.6493 0.06786 0.06282 -0.0374 1.0000 0.0276
-9.000 -0.6585 0.06367 0.05850 -0.0394 1.0000 0.0269
-8.750 -0.6630 0.05950 0.05415 -0.0407 1.0000 0.0260
-8.500 -0.6637 0.05540 0.04980 -0.0415 1.0000 0.0249
-8.250 -0.6605 0.05136 0.04544 -0.0418 1.0000 0.0237
-8.000 -0.6535 0.04744 0.04111 -0.0416 1.0000 0.0223
-7.750 -0.6425 0.04383 0.03696 -0.0410 1.0000 0.0208
-7.500 -0.6267 0.04112 0.03368 -0.0400 1.0000 0.0198
-7.250 -0.6085 0.03892 0.03112 -0.0392 1.0000 0.0194
-7.000 -0.5898 0.03662 0.02850 -0.0384 1.0000 0.0192
-6.750 -0.5719 0.03370 0.02531 -0.0376 1.0000 0.0198
-6.500 -0.5527 0.03131 0.02273 -0.0368 1.0000 0.0207
-6.250 -0.5320 0.02938 0.02062 -0.0359 1.0000 0.0215
-6.000 -0.5103 0.02762 0.01871 -0.0347 1.0000 0.0216
-5.750 -0.4886 0.02603 0.01701 -0.0335 1.0000 0.0217
-5.500 -0.4673 0.02460 0.01552 -0.0322 1.0000 0.0219
-5.250 -0.4468 0.02332 0.01418 -0.0308 1.0000 0.0223
-5.000 -0.4270 0.02217 0.01304 -0.0295 1.0000 0.0229
-4.750 -0.4074 0.02119 0.01203 -0.0283 1.0000 0.0245
-4.500 -0.3873 0.02033 0.01110 -0.0272 1.0000 0.0264
-4.250 -0.3664 0.01953 0.01017 -0.0264 1.0000 0.0275
-4.000 -0.3445 0.01882 0.00930 -0.0257 1.0000 0.0286
-3.750 -0.3219 0.01819 0.00847 -0.0252 1.0000 0.0302
-3.500 -0.2825 0.01739 0.00749 -0.0280 0.9930 0.0371
-3.250 -0.2405 0.01648 0.00661 -0.0314 0.9842 0.0624
-3.000 -0.2033 0.01480 0.00672 -0.0349 0.9748 0.4853
-2.750 -0.1630 0.01515 0.00696 -0.0370 0.9647 0.5250
-2.500 -0.1294 0.01571 0.00762 -0.0373 0.9533 0.5686
-2.250 -0.0949 0.01566 0.00743 -0.0385 0.9421 0.5794
-2.000 -0.0601 0.01552 0.00717 -0.0399 0.9308 0.5843
-1.750 -0.0255 0.01538 0.00688 -0.0413 0.9190 0.5894
-1.500 0.0075 0.01522 0.00664 -0.0423 0.9065 0.5930
-1.250 0.0393 0.01509 0.00644 -0.0430 0.8929 0.5967
-1.000 0.0700 0.01497 0.00624 -0.0434 0.8780 0.6008
-0.750 0.1001 0.01486 0.00603 -0.0438 0.8623 0.6050
-0.500 0.1289 0.01475 0.00590 -0.0438 0.8462 0.6082
-0.250 0.1576 0.01465 0.00577 -0.0437 0.8296 0.6119
0.000 0.1862 0.01457 0.00563 -0.0436 0.8119 0.6158
0.250 0.2143 0.01451 0.00550 -0.0435 0.7925 0.6199
0.500 0.2416 0.01444 0.00541 -0.0431 0.7721 0.6235
0.750 0.2690 0.01440 0.00532 -0.0427 0.7518 0.6276
1.000 0.2964 0.01439 0.00525 -0.0424 0.7298 0.6319
1.250 0.3236 0.01439 0.00521 -0.0420 0.7093 0.6359
1.500 0.3506 0.01441 0.00521 -0.0417 0.6893 0.6403
1.750 0.3778 0.01447 0.00523 -0.0414 0.6700 0.6455
2.000 0.4047 0.01454 0.00528 -0.0410 0.6505 0.6504
2.250 0.4315 0.01461 0.00536 -0.0407 0.6299 0.6554
2.500 0.4587 0.01472 0.00545 -0.0405 0.6107 0.6613
2.750 0.4859 0.01482 0.00561 -0.0403 0.5936 0.6672
3.000 0.5131 0.01494 0.00577 -0.0401 0.5771 0.6744
3.250 0.5402 0.01504 0.00597 -0.0400 0.5602 0.6818
3.500 0.5673 0.01516 0.00620 -0.0398 0.5428 0.6906
3.750 0.5939 0.01527 0.00642 -0.0395 0.5248 0.6998
4.000 0.6202 0.01539 0.00664 -0.0391 0.5063 0.7113
4.250 0.6459 0.01552 0.00690 -0.0387 0.4862 0.7261
4.500 0.6708 0.01565 0.00715 -0.0380 0.4643 0.7464
4.750 0.6943 0.01577 0.00743 -0.0370 0.4403 0.7779
5.000 0.7166 0.01581 0.00769 -0.0355 0.4170 0.8510
5.250 0.7468 0.01602 0.00807 -0.0361 0.3916 1.0000
5.500 0.7725 0.01643 0.00848 -0.0360 0.3623 1.0000
5.750 0.7975 0.01687 0.00888 -0.0357 0.3249 1.0000
6.000 0.8214 0.01741 0.00930 -0.0353 0.2872 1.0000
6.250 0.8447 0.01806 0.00985 -0.0349 0.2574 1.0000
6.500 0.8675 0.01881 0.01058 -0.0344 0.2307 1.0000
6.750 0.8906 0.01955 0.01135 -0.0339 0.2048 1.0000
7.000 0.9136 0.02029 0.01217 -0.0334 0.1752 1.0000
7.250 0.9341 0.02131 0.01297 -0.0328 0.1271 1.0000
7.500 0.9511 0.02277 0.01411 -0.0319 0.0898 1.0000
7.750 0.9697 0.02405 0.01533 -0.0311 0.0649 1.0000
8.000 0.9866 0.02553 0.01681 -0.0299 0.0472 1.0000
8.250 1.0017 0.02718 0.01849 -0.0286 0.0354 1.0000
8.500 1.0148 0.02894 0.02037 -0.0270 0.0300 1.0000
8.750 1.0292 0.03050 0.02215 -0.0255 0.0260 1.0000
9.000 1.0417 0.03212 0.02385 -0.0241 0.0229 1.0000
9.250 1.0518 0.03404 0.02591 -0.0223 0.0212 1.0000
9.500 1.0624 0.03602 0.02812 -0.0205 0.0201 1.0000
9.750 1.0724 0.03820 0.03051 -0.0187 0.0191 1.0000
10.000 1.0813 0.04046 0.03299 -0.0169 0.0181 1.0000
10.250 1.0871 0.04267 0.03543 -0.0150 0.0171 1.0000
10.500 1.0905 0.04495 0.03791 -0.0133 0.0161 1.0000
10.750 1.0914 0.04743 0.04059 -0.0119 0.0154 1.0000
11.000 1.0897 0.05026 0.04362 -0.0108 0.0148 1.0000
11.250 1.0853 0.05360 0.04718 -0.0100 0.0144 1.0000
11.500 1.0783 0.05741 0.05124 -0.0098 0.0142 1.0000
11.750 1.0689 0.06170 0.05578 -0.0103 0.0141 1.0000
12.000 1.0573 0.06649 0.06082 -0.0116 0.0140 1.0000
12.250 1.0439 0.07183 0.06640 -0.0138 0.0140 1.0000
12.500 1.0290 0.07778 0.07258 -0.0168 0.0140 1.0000
12.750 1.0127 0.08436 0.07937 -0.0205 0.0140 1.0000
13.000 0.9949 0.09177 0.08700 -0.0251 0.0141 1.0000
13.250 0.9743 0.10036 0.09579 -0.0307 0.0143 1.0000
13.500 0.9476 0.11130 0.10694 -0.0378 0.0147 1.0000
13.750 0.8935 0.13246 0.12828 -0.0503 0.0165 1.0000
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