GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 200,000 Max Cl/Cd: 67.45 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795-il-200000-n5.txt Download as CSV file: xf-goe795-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4793 0.08469 0.08117 -0.0312 1.0000 0.0196
-8.750 -0.4901 0.07951 0.07607 -0.0333 1.0000 0.0193
-8.500 -0.5058 0.07447 0.07111 -0.0351 1.0000 0.0191
-8.250 -0.5213 0.06873 0.06543 -0.0379 1.0000 0.0188
-8.000 -0.5316 0.06194 0.05863 -0.0413 1.0000 0.0185
-7.750 -0.5413 0.05449 0.05107 -0.0435 1.0000 0.0184
-7.250 -0.5603 0.04081 0.03677 -0.0429 1.0000 0.0185
-7.000 -0.5613 0.03646 0.03206 -0.0410 1.0000 0.0189
-6.750 -0.5520 0.03455 0.02999 -0.0394 0.9999 0.0195
-6.500 -0.5276 0.03023 0.02511 -0.0413 0.9958 0.0198
-6.250 -0.5032 0.02628 0.02052 -0.0423 0.9916 0.0198
-6.000 -0.4764 0.02362 0.01737 -0.0429 0.9872 0.0198
-5.750 -0.4468 0.02161 0.01496 -0.0438 0.9835 0.0200
-5.500 -0.4180 0.02009 0.01316 -0.0444 0.9793 0.0204
-5.250 -0.3891 0.01880 0.01163 -0.0448 0.9745 0.0209
-5.000 -0.3576 0.01768 0.01029 -0.0457 0.9708 0.0216
-4.750 -0.3279 0.01673 0.00918 -0.0462 0.9661 0.0225
-4.500 -0.2983 0.01589 0.00820 -0.0466 0.9608 0.0238
-4.250 -0.2656 0.01512 0.00730 -0.0476 0.9571 0.0254
-4.000 -0.2363 0.01452 0.00660 -0.0479 0.9515 0.0272
-3.750 -0.2055 0.01384 0.00588 -0.0486 0.9464 0.0332
-3.500 -0.1713 0.01332 0.00526 -0.0499 0.9431 0.0416
-3.250 -0.1424 0.01288 0.00478 -0.0501 0.9364 0.0509
-2.750 -0.0741 0.01215 0.00413 -0.0529 0.9273 0.0838
-2.500 -0.0443 0.01189 0.00387 -0.0533 0.9195 0.1056
-2.250 -0.0095 0.01151 0.00361 -0.0549 0.9149 0.1357
-2.000 0.0187 0.01123 0.00345 -0.0550 0.9057 0.1681
-1.750 0.0516 0.01091 0.00326 -0.0561 0.8992 0.2149
-1.500 0.0811 0.01061 0.00308 -0.0565 0.8903 0.2601
-1.250 0.1097 0.01021 0.00294 -0.0567 0.8812 0.3353
-1.000 0.1355 0.00950 0.00283 -0.0564 0.8718 0.5057
-0.750 0.1601 0.00856 0.00282 -0.0552 0.8607 0.7727
-0.500 0.2715 0.00828 0.00275 -0.0728 0.8556 0.9560
-0.250 0.3147 0.00831 0.00267 -0.0759 0.8393 0.9864
0.000 0.3589 0.00833 0.00257 -0.0793 0.8230 1.0000
0.250 0.3852 0.00835 0.00249 -0.0789 0.8075 1.0000
0.500 0.4107 0.00840 0.00245 -0.0783 0.7937 1.0000
0.750 0.4359 0.00846 0.00244 -0.0776 0.7804 1.0000
1.000 0.4608 0.00853 0.00244 -0.0769 0.7671 1.0000
1.250 0.4854 0.00861 0.00246 -0.0761 0.7536 1.0000
1.500 0.5096 0.00871 0.00248 -0.0752 0.7383 1.0000
1.750 0.5331 0.00883 0.00253 -0.0740 0.7189 1.0000
2.000 0.5557 0.00897 0.00256 -0.0727 0.6948 1.0000
2.250 0.5779 0.00912 0.00262 -0.0713 0.6686 1.0000
2.500 0.6004 0.00927 0.00270 -0.0701 0.6454 1.0000
2.750 0.6226 0.00943 0.00279 -0.0688 0.6197 1.0000
3.000 0.6444 0.00962 0.00292 -0.0673 0.5897 1.0000
3.250 0.6651 0.00986 0.00303 -0.0657 0.5523 1.0000
3.500 0.6846 0.01018 0.00316 -0.0639 0.5048 1.0000
3.750 0.7023 0.01062 0.00334 -0.0618 0.4479 1.0000
4.000 0.7197 0.01113 0.00359 -0.0597 0.3929 1.0000
4.250 0.7382 0.01163 0.00392 -0.0579 0.3497 1.0000
4.500 0.7579 0.01207 0.00423 -0.0564 0.3139 1.0000
4.750 0.7774 0.01255 0.00457 -0.0548 0.2743 1.0000
5.000 0.7968 0.01305 0.00492 -0.0533 0.2283 1.0000
5.250 0.8145 0.01371 0.00534 -0.0516 0.1784 1.0000
5.500 0.8332 0.01432 0.00583 -0.0500 0.1458 1.0000
5.750 0.8524 0.01492 0.00637 -0.0485 0.1162 1.0000
6.000 0.8713 0.01553 0.00689 -0.0469 0.0913 1.0000
6.250 0.8906 0.01612 0.00746 -0.0454 0.0778 1.0000
6.500 0.9101 0.01668 0.00805 -0.0439 0.0687 1.0000
6.750 0.9293 0.01725 0.00862 -0.0424 0.0590 1.0000
7.000 0.9478 0.01788 0.00922 -0.0409 0.0503 1.0000
7.250 0.9665 0.01850 0.00989 -0.0394 0.0443 1.0000
7.500 0.9856 0.01907 0.01059 -0.0380 0.0367 1.0000
7.750 1.0051 0.01964 0.01124 -0.0366 0.0264 1.0000
8.000 1.0224 0.02041 0.01196 -0.0349 0.0177 1.0000
8.250 1.0370 0.02143 0.01295 -0.0328 0.0125 1.0000
8.500 1.0519 0.02239 0.01405 -0.0307 0.0110 1.0000
8.750 1.0658 0.02343 0.01523 -0.0285 0.0100 1.0000
9.000 1.0778 0.02462 0.01655 -0.0260 0.0093 1.0000
9.250 1.0854 0.02619 0.01827 -0.0231 0.0086 1.0000
9.500 1.0930 0.02774 0.01997 -0.0201 0.0083 1.0000
9.750 1.1013 0.02918 0.02160 -0.0172 0.0080 1.0000
10.000 1.1093 0.03069 0.02334 -0.0145 0.0078 1.0000
10.250 1.1158 0.03246 0.02531 -0.0117 0.0076 1.0000
10.500 1.1216 0.03431 0.02738 -0.0090 0.0075 1.0000
10.750 1.1251 0.03643 0.02975 -0.0063 0.0073 1.0000
11.000 1.1274 0.03846 0.03201 -0.0038 0.0070 1.0000
11.250 1.1283 0.04050 0.03426 -0.0015 0.0068 1.0000
11.500 1.1258 0.04299 0.03701 0.0008 0.0066 1.0000
11.750 1.1236 0.04523 0.03943 0.0025 0.0063 1.0000
12.000 1.1151 0.04859 0.04307 0.0041 0.0064 1.0000
12.250 1.1086 0.05156 0.04623 0.0048 0.0061 1.0000
12.500 1.0945 0.05595 0.05090 0.0051 0.0063 1.0000
12.750 1.0951 0.05799 0.05295 0.0045 0.0057 1.0000
13.000 1.0697 0.06490 0.06026 0.0030 0.0061 1.0000
13.250 1.0618 0.06909 0.06455 0.0011 0.0058 1.0000
13.500 1.0542 0.07347 0.06898 -0.0014 0.0055 1.0000
13.750 1.0137 0.08556 0.08152 -0.0078 0.0061 1.0000
14.000 0.9744 0.09913 0.09537 -0.0162 0.0068 1.0000
14.250 0.9496 0.11052 0.10688 -0.0231 0.0067 1.0000
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Polar data table (+)
Polar graphs
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