GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 100,000 Max Cl/Cd: 53.56 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795-il-100000-n5.txt Download as CSV file: xf-goe795-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4574 0.08969 0.08468 -0.0306 1.0000 0.0360
-8.500 -0.4612 0.08597 0.08103 -0.0318 1.0000 0.0359
-8.250 -0.4670 0.08236 0.07749 -0.0326 1.0000 0.0355
-8.000 -0.4757 0.07887 0.07408 -0.0333 1.0000 0.0350
-7.750 -0.4818 0.07463 0.06990 -0.0351 1.0000 0.0345
-7.500 -0.4863 0.07014 0.06544 -0.0369 1.0000 0.0339
-7.250 -0.4902 0.06526 0.06053 -0.0386 1.0000 0.0333
-7.000 -0.4927 0.06018 0.05539 -0.0398 1.0000 0.0326
-6.750 -0.4940 0.05485 0.04992 -0.0405 1.0000 0.0321
-6.500 -0.4937 0.04941 0.04426 -0.0404 1.0000 0.0314
-6.250 -0.4918 0.04398 0.03849 -0.0397 1.0000 0.0310
-6.000 -0.4871 0.03905 0.03311 -0.0383 1.0000 0.0307
-5.750 -0.4789 0.03498 0.02855 -0.0366 1.0000 0.0306
-5.500 -0.4672 0.03180 0.02489 -0.0347 1.0000 0.0308
-5.250 -0.4530 0.02917 0.02180 -0.0329 1.0000 0.0312
-5.000 -0.4369 0.02701 0.01921 -0.0312 1.0000 0.0319
-4.750 -0.4171 0.02511 0.01687 -0.0300 0.9994 0.0328
-4.500 -0.3842 0.02326 0.01460 -0.0312 0.9950 0.0345
-4.250 -0.3512 0.02199 0.01296 -0.0324 0.9901 0.0376
-4.000 -0.3191 0.02064 0.01146 -0.0336 0.9851 0.0414
-3.750 -0.2862 0.01959 0.01029 -0.0347 0.9801 0.0461
-3.500 -0.2551 0.01858 0.00913 -0.0354 0.9740 0.0523
-3.250 -0.2204 0.01791 0.00835 -0.0370 0.9691 0.0638
-3.000 -0.1903 0.01744 0.00794 -0.0377 0.9616 0.0798
-2.750 -0.1553 0.01701 0.00750 -0.0393 0.9565 0.1053
-2.500 -0.1259 0.01648 0.00702 -0.0398 0.9488 0.1305
-2.250 -0.0913 0.01604 0.00669 -0.0414 0.9436 0.1647
-2.000 -0.0608 0.01570 0.00640 -0.0421 0.9360 0.2011
-1.750 -0.0264 0.01521 0.00615 -0.0436 0.9305 0.2667
-1.500 0.0047 0.01447 0.00598 -0.0447 0.9240 0.4034
-1.250 0.0902 0.01295 0.00603 -0.0558 0.9318 0.9454
-1.000 0.1415 0.01302 0.00588 -0.0608 0.9298 1.0000
-0.750 0.1742 0.01301 0.00572 -0.0618 0.9208 1.0000
-0.500 0.2134 0.01295 0.00551 -0.0642 0.9149 1.0000
-0.250 0.2439 0.01295 0.00540 -0.0647 0.9046 1.0000
0.000 0.2771 0.01291 0.00527 -0.0657 0.8949 1.0000
0.250 0.3125 0.01280 0.00507 -0.0670 0.8833 1.0000
0.500 0.3461 0.01267 0.00487 -0.0678 0.8683 1.0000
0.750 0.3780 0.01258 0.00471 -0.0683 0.8530 1.0000
1.000 0.4085 0.01256 0.00466 -0.0686 0.8400 1.0000
1.250 0.4383 0.01257 0.00463 -0.0688 0.8282 1.0000
1.500 0.4678 0.01259 0.00463 -0.0689 0.8162 1.0000
1.750 0.4967 0.01263 0.00465 -0.0689 0.8039 1.0000
2.000 0.5246 0.01268 0.00473 -0.0687 0.7911 1.0000
2.250 0.5518 0.01276 0.00481 -0.0683 0.7776 1.0000
2.500 0.5786 0.01285 0.00491 -0.0678 0.7636 1.0000
2.750 0.6045 0.01295 0.00503 -0.0672 0.7481 1.0000
3.000 0.6290 0.01306 0.00518 -0.0661 0.7279 1.0000
3.250 0.6530 0.01315 0.00523 -0.0648 0.7006 1.0000
3.500 0.6756 0.01327 0.00527 -0.0631 0.6674 1.0000
3.750 0.6966 0.01344 0.00538 -0.0613 0.6315 1.0000
4.000 0.7183 0.01364 0.00553 -0.0597 0.5971 1.0000
4.250 0.7396 0.01388 0.00573 -0.0581 0.5609 1.0000
4.500 0.7600 0.01419 0.00598 -0.0563 0.5172 1.0000
4.750 0.7791 0.01461 0.00623 -0.0544 0.4666 1.0000
5.000 0.7961 0.01520 0.00654 -0.0522 0.4086 1.0000
5.250 0.8121 0.01590 0.00697 -0.0499 0.3520 1.0000
5.500 0.8292 0.01659 0.00748 -0.0480 0.3033 1.0000
5.750 0.8465 0.01730 0.00803 -0.0462 0.2488 1.0000
6.000 0.8623 0.01818 0.00869 -0.0442 0.1905 1.0000
6.250 0.8781 0.01915 0.00946 -0.0422 0.1503 1.0000
6.500 0.8947 0.02009 0.01032 -0.0404 0.1207 1.0000
6.750 0.9110 0.02106 0.01123 -0.0385 0.1030 1.0000
7.000 0.9277 0.02197 0.01218 -0.0366 0.0916 1.0000
7.250 0.9444 0.02288 0.01317 -0.0347 0.0816 1.0000
7.500 0.9608 0.02379 0.01413 -0.0330 0.0703 1.0000
7.750 0.9776 0.02464 0.01504 -0.0315 0.0559 1.0000
8.000 0.9917 0.02577 0.01622 -0.0295 0.0462 1.0000
8.250 1.0021 0.02736 0.01791 -0.0269 0.0373 1.0000
8.500 1.0135 0.02879 0.01936 -0.0246 0.0297 1.0000
8.750 1.0281 0.03010 0.02090 -0.0225 0.0244 1.0000
9.000 1.0400 0.03154 0.02244 -0.0203 0.0219 1.0000
9.250 1.0499 0.03350 0.02452 -0.0180 0.0202 1.0000
9.500 1.0630 0.03544 0.02673 -0.0159 0.0185 1.0000
9.750 1.0730 0.03692 0.02841 -0.0137 0.0163 1.0000
10.000 1.0802 0.03836 0.02999 -0.0113 0.0151 1.0000
10.250 1.0839 0.04030 0.03208 -0.0087 0.0142 1.0000
10.500 1.0854 0.04306 0.03514 -0.0061 0.0137 1.0000
10.750 1.0849 0.04607 0.03845 -0.0035 0.0134 1.0000
11.000 1.0819 0.04901 0.04170 -0.0010 0.0132 1.0000
11.250 1.0752 0.05217 0.04517 0.0012 0.0131 1.0000
11.500 1.0651 0.05566 0.04896 0.0030 0.0131 1.0000
11.750 1.0526 0.05946 0.05303 0.0040 0.0130 1.0000
12.000 1.0381 0.06368 0.05751 0.0041 0.0130 1.0000
12.250 1.0213 0.06855 0.06262 0.0033 0.0130 1.0000
12.500 1.0038 0.07393 0.06821 0.0014 0.0130 1.0000
12.750 0.9845 0.08023 0.07471 -0.0017 0.0131 1.0000
13.000 0.9655 0.08723 0.08187 -0.0058 0.0132 1.0000
13.250 0.9451 0.09542 0.09020 -0.0110 0.0133 1.0000
13.500 0.9250 0.10453 0.09941 -0.0169 0.0135 1.0000
13.750 0.9046 0.11479 0.10973 -0.0232 0.0136 1.0000
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