GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 500,000 Max Cl/Cd: 81.6 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe632-il-500000-n5.txt Download as CSV file: xf-goe632-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3623 0.10614 0.10366 -0.0452 1.0000 0.0214
-11.750 -0.3589 0.10363 0.10117 -0.0457 1.0000 0.0217
-11.250 -0.6820 0.03499 0.03132 -0.0820 0.9550 0.0244
-11.000 -0.6718 0.03092 0.02671 -0.0832 0.9402 0.0247
-10.750 -0.6507 0.02793 0.02339 -0.0850 0.9237 0.0250
-10.500 -0.6218 0.02628 0.02155 -0.0869 0.9038 0.0253
-10.250 -0.5983 0.02500 0.02003 -0.0872 0.8816 0.0255
-10.000 -0.5793 0.02417 0.01900 -0.0862 0.8614 0.0257
-9.750 -0.5633 0.02338 0.01804 -0.0844 0.8457 0.0259
-9.500 -0.5468 0.02275 0.01726 -0.0826 0.8333 0.0262
-9.250 -0.5305 0.02201 0.01634 -0.0807 0.8225 0.0265
-9.000 -0.5140 0.02122 0.01536 -0.0788 0.8118 0.0268
-8.750 -0.4964 0.02045 0.01443 -0.0770 0.8025 0.0271
-8.500 -0.4782 0.01968 0.01348 -0.0754 0.7930 0.0273
-8.250 -0.4588 0.01896 0.01260 -0.0739 0.7843 0.0276
-8.000 -0.4387 0.01829 0.01177 -0.0725 0.7755 0.0279
-7.750 -0.4177 0.01766 0.01101 -0.0712 0.7663 0.0281
-7.500 -0.3963 0.01710 0.01029 -0.0700 0.7572 0.0284
-7.250 -0.3742 0.01656 0.00964 -0.0689 0.7476 0.0286
-7.000 -0.3518 0.01609 0.00904 -0.0678 0.7383 0.0289
-6.750 -0.3291 0.01567 0.00850 -0.0667 0.7277 0.0291
-6.500 -0.3064 0.01519 0.00793 -0.0657 0.7174 0.0294
-6.250 -0.2842 0.01466 0.00731 -0.0646 0.7069 0.0298
-6.000 -0.2614 0.01429 0.00689 -0.0636 0.6961 0.0303
-5.750 -0.2383 0.01399 0.00652 -0.0626 0.6861 0.0307
-5.500 -0.2153 0.01369 0.00614 -0.0616 0.6764 0.0310
-5.250 -0.1917 0.01340 0.00581 -0.0607 0.6680 0.0315
-5.000 -0.1683 0.01315 0.00548 -0.0597 0.6601 0.0319
-4.750 -0.1444 0.01289 0.00517 -0.0589 0.6533 0.0324
-4.500 -0.1207 0.01265 0.00487 -0.0580 0.6463 0.0327
-4.250 -0.0969 0.01245 0.00460 -0.0571 0.6401 0.0333
-4.000 -0.0726 0.01223 0.00435 -0.0563 0.6338 0.0338
-3.750 -0.0486 0.01205 0.00411 -0.0554 0.6278 0.0343
-3.500 -0.0248 0.01183 0.00386 -0.0545 0.6224 0.0350
-3.250 -0.0004 0.01164 0.00365 -0.0537 0.6169 0.0358
-3.000 0.0239 0.01149 0.00349 -0.0529 0.6111 0.0370
-2.750 0.0483 0.01138 0.00334 -0.0522 0.6061 0.0384
-2.500 0.0732 0.01125 0.00319 -0.0515 0.6008 0.0396
-2.250 0.0977 0.01112 0.00306 -0.0507 0.5955 0.0413
-2.000 0.1220 0.01102 0.00295 -0.0499 0.5907 0.0440
-1.750 0.1470 0.01091 0.00285 -0.0492 0.5858 0.0476
-1.500 0.1717 0.01082 0.00278 -0.0485 0.5802 0.0533
-1.250 0.1961 0.01075 0.00272 -0.0478 0.5752 0.0603
-1.000 0.2208 0.01069 0.00267 -0.0471 0.5705 0.0666
-0.750 0.2458 0.01063 0.00261 -0.0464 0.5647 0.0731
-0.500 0.2698 0.01056 0.00255 -0.0456 0.5588 0.0798
-0.250 0.2942 0.01052 0.00250 -0.0448 0.5535 0.0859
0.000 0.3186 0.01044 0.00246 -0.0440 0.5477 0.0957
0.250 0.3413 0.01032 0.00243 -0.0430 0.5417 0.1257
0.500 0.3598 0.00994 0.00240 -0.0412 0.5349 0.2417
0.750 0.3747 0.00952 0.00243 -0.0386 0.5259 0.3921
1.000 0.3880 0.00914 0.00238 -0.0356 0.5155 0.5007
1.500 0.4971 0.00866 0.00305 -0.0469 0.4897 0.9243
1.750 0.5240 0.00884 0.00317 -0.0466 0.4787 0.9314
2.000 0.5554 0.00905 0.00331 -0.0473 0.4688 0.9348
2.250 0.5810 0.00923 0.00343 -0.0468 0.4593 0.9399
2.500 0.6079 0.00944 0.00359 -0.0465 0.4506 0.9458
2.750 0.6421 0.00969 0.00377 -0.0479 0.4390 0.9484
3.000 0.6714 0.00993 0.00392 -0.0483 0.4257 0.9514
3.250 0.6942 0.01010 0.00405 -0.0473 0.4163 0.9562
3.500 0.7247 0.01034 0.00423 -0.0479 0.4079 0.9598
3.750 0.7581 0.01056 0.00440 -0.0493 0.3967 0.9616
4.000 0.7887 0.01074 0.00455 -0.0500 0.3883 0.9637
4.250 0.8154 0.01091 0.00469 -0.0500 0.3804 0.9660
4.500 0.8365 0.01108 0.00483 -0.0487 0.3738 0.9697
4.750 0.8619 0.01127 0.00499 -0.0484 0.3641 0.9720
5.000 0.8938 0.01148 0.00516 -0.0495 0.3544 0.9734
5.250 0.9233 0.01171 0.00534 -0.0502 0.3438 0.9751
5.500 0.9505 0.01188 0.00550 -0.0503 0.3355 0.9768
5.750 0.9741 0.01210 0.00569 -0.0497 0.3253 0.9788
6.000 0.9956 0.01232 0.00589 -0.0487 0.3154 0.9815
6.250 1.0189 0.01255 0.00609 -0.0480 0.3065 0.9835
6.500 1.0453 0.01281 0.00631 -0.0482 0.2937 0.9846
6.750 1.0701 0.01312 0.00656 -0.0481 0.2760 0.9860
7.000 1.0911 0.01360 0.00690 -0.0473 0.2482 0.9880
7.250 1.0993 0.01466 0.00762 -0.0445 0.1873 0.9916
7.500 1.1156 0.01519 0.00807 -0.0429 0.1713 0.9940
7.750 1.1366 0.01564 0.00847 -0.0423 0.1594 0.9960
8.000 1.1572 0.01607 0.00888 -0.0416 0.1506 0.9980
8.250 1.1781 0.01649 0.00929 -0.0410 0.1409 0.9996
8.500 1.1846 0.01696 0.00974 -0.0375 0.1326 1.0000
8.750 1.1873 0.01740 0.01017 -0.0333 0.1231 1.0000
9.000 1.1881 0.01799 0.01072 -0.0289 0.1119 1.0000
9.250 1.1888 0.01867 0.01134 -0.0247 0.1021 1.0000
9.750 1.1958 0.02007 0.01273 -0.0177 0.0920 1.0000
10.000 1.2018 0.02079 0.01347 -0.0148 0.0899 1.0000
10.250 1.2070 0.02161 0.01432 -0.0120 0.0875 1.0000
10.500 1.2131 0.02248 0.01521 -0.0095 0.0855 1.0000
10.750 1.2198 0.02338 0.01615 -0.0072 0.0841 1.0000
11.000 1.2277 0.02428 0.01710 -0.0051 0.0825 1.0000
11.250 1.2360 0.02520 0.01808 -0.0032 0.0820 1.0000
11.500 1.2438 0.02621 0.01915 -0.0014 0.0804 1.0000
11.750 1.2511 0.02731 0.02029 0.0003 0.0790 1.0000
12.000 1.2573 0.02853 0.02156 0.0020 0.0775 1.0000
12.250 1.2619 0.02992 0.02300 0.0037 0.0756 1.0000
12.500 1.2669 0.03136 0.02448 0.0052 0.0742 1.0000
12.750 1.2694 0.03304 0.02621 0.0067 0.0721 1.0000
13.000 1.2795 0.03417 0.02740 0.0077 0.0709 1.0000
13.250 1.2875 0.03550 0.02880 0.0087 0.0693 1.0000
13.500 1.2945 0.03695 0.03033 0.0097 0.0673 1.0000
13.750 1.2979 0.03877 0.03216 0.0107 0.0631 1.0000
14.000 1.3037 0.04041 0.03385 0.0115 0.0602 1.0000
14.250 1.3049 0.04251 0.03590 0.0124 0.0481 1.0000
14.500 1.2862 0.04661 0.03982 0.0136 0.0271 1.0000
14.750 1.2748 0.05013 0.04335 0.0145 0.0203 1.0000
15.000 1.2742 0.05268 0.04595 0.0150 0.0188 1.0000
15.250 1.2723 0.05541 0.04874 0.0155 0.0172 1.0000
15.500 1.2719 0.05804 0.05144 0.0158 0.0162 1.0000
15.750 1.2716 0.06071 0.05419 0.0160 0.0155 1.0000
16.000 1.2717 0.06338 0.05693 0.0161 0.0151 1.0000
16.250 1.2683 0.06654 0.06017 0.0161 0.0142 1.0000
16.500 1.2677 0.06941 0.06311 0.0160 0.0140 1.0000
16.750 1.2674 0.07229 0.06609 0.0159 0.0136 1.0000
17.000 1.2668 0.07526 0.06914 0.0156 0.0132 1.0000
17.250 1.2652 0.07840 0.07236 0.0153 0.0128 1.0000
17.500 1.2628 0.08169 0.07574 0.0148 0.0126 1.0000
17.750 1.2599 0.08509 0.07923 0.0143 0.0124 1.0000
18.000 1.2555 0.08872 0.08295 0.0136 0.0121 1.0000
18.250 1.2503 0.09254 0.08685 0.0129 0.0118 1.0000
18.500 1.2423 0.09685 0.09124 0.0118 0.0114 1.0000
18.750 1.2357 0.10097 0.09546 0.0108 0.0114 1.0000
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Polar data table (+)
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