GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 500,000 Max Cl/Cd: 94.08 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe633-il-500000.txt Download as CSV file: xf-goe633-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2854 0.09093 0.08794 -0.0518 0.8121 0.0474
-10.250 -0.6120 0.04017 0.03632 -0.0749 0.7988 0.0385
-10.000 -0.6248 0.03652 0.03236 -0.0717 0.7890 0.0376
-9.750 -0.6374 0.03258 0.02793 -0.0680 0.7805 0.0366
-9.500 -0.6394 0.02949 0.02434 -0.0647 0.7733 0.0360
-9.250 -0.6278 0.02769 0.02226 -0.0626 0.7660 0.0360
-9.000 -0.6116 0.02641 0.02078 -0.0610 0.7595 0.0362
-8.750 -0.5932 0.02527 0.01951 -0.0597 0.7529 0.0366
-8.500 -0.5745 0.02413 0.01819 -0.0583 0.7465 0.0368
-8.250 -0.5554 0.02297 0.01680 -0.0569 0.7409 0.0369
-8.000 -0.5346 0.02187 0.01556 -0.0557 0.7351 0.0370
-7.750 -0.5127 0.02094 0.01448 -0.0546 0.7294 0.0372
-7.500 -0.4903 0.02009 0.01346 -0.0535 0.7240 0.0374
-7.250 -0.4669 0.01927 0.01254 -0.0526 0.7184 0.0377
-7.000 -0.4431 0.01853 0.01169 -0.0518 0.7127 0.0380
-6.750 -0.4189 0.01787 0.01091 -0.0509 0.7077 0.0382
-6.500 -0.3941 0.01727 0.01022 -0.0502 0.7027 0.0386
-6.250 -0.3689 0.01678 0.00965 -0.0495 0.6973 0.0391
-6.000 -0.3435 0.01636 0.00915 -0.0488 0.6920 0.0394
-5.750 -0.3183 0.01586 0.00854 -0.0481 0.6870 0.0398
-5.500 -0.2941 0.01500 0.00769 -0.0473 0.6820 0.0403
-5.250 -0.2694 0.01441 0.00709 -0.0466 0.6768 0.0408
-5.000 -0.2445 0.01397 0.00660 -0.0458 0.6713 0.0413
-4.750 -0.2191 0.01358 0.00619 -0.0451 0.6653 0.0420
-4.500 -0.1934 0.01321 0.00579 -0.0445 0.6588 0.0427
-4.250 -0.1677 0.01290 0.00542 -0.0438 0.6529 0.0434
-4.000 -0.1416 0.01260 0.00509 -0.0432 0.6466 0.0443
-3.750 -0.1151 0.01233 0.00479 -0.0426 0.6404 0.0452
-3.500 -0.0895 0.01198 0.00438 -0.0420 0.6351 0.0466
-3.250 -0.0630 0.01170 0.00410 -0.0415 0.6300 0.0484
-3.000 -0.0361 0.01147 0.00385 -0.0410 0.6247 0.0503
-2.750 -0.0092 0.01126 0.00360 -0.0406 0.6196 0.0529
-2.500 0.0174 0.01103 0.00335 -0.0401 0.6145 0.0583
-2.250 0.0427 0.01054 0.00314 -0.0395 0.6089 0.1092
-2.000 0.0686 0.01024 0.00303 -0.0390 0.6034 0.1529
-1.750 0.0957 0.01019 0.00302 -0.0386 0.5984 0.1820
-1.500 0.1233 0.01014 0.00302 -0.0383 0.5931 0.1979
-1.250 0.1506 0.01009 0.00299 -0.0380 0.5874 0.2099
-1.000 0.1780 0.01010 0.00294 -0.0376 0.5819 0.2193
-0.750 0.2052 0.01004 0.00292 -0.0373 0.5760 0.2292
-0.500 0.2327 0.01002 0.00288 -0.0370 0.5698 0.2368
-0.250 0.2594 0.00999 0.00284 -0.0366 0.5642 0.2464
0.000 0.2869 0.00997 0.00283 -0.0363 0.5583 0.2543
0.250 0.3136 0.00990 0.00280 -0.0359 0.5520 0.2641
0.500 0.3404 0.00993 0.00277 -0.0354 0.5459 0.2738
0.750 0.3672 0.00984 0.00277 -0.0350 0.5390 0.2842
1.000 0.3937 0.00981 0.00273 -0.0346 0.5318 0.2940
1.250 0.4200 0.00977 0.00272 -0.0341 0.5246 0.3056
1.500 0.4461 0.00971 0.00271 -0.0336 0.5167 0.3207
1.750 0.4714 0.00964 0.00271 -0.0329 0.5089 0.3467
2.000 0.4941 0.00937 0.00273 -0.0319 0.4996 0.4277
2.250 0.5438 0.00833 0.00313 -0.0360 0.4881 0.9415
2.500 0.5959 0.00871 0.00343 -0.0406 0.4748 0.9628
2.750 0.6596 0.00907 0.00368 -0.0478 0.4580 0.9757
3.000 0.7092 0.00931 0.00382 -0.0522 0.4426 0.9834
3.250 0.7650 0.00950 0.00390 -0.0580 0.4258 0.9908
3.500 0.8157 0.00960 0.00389 -0.0629 0.4093 0.9965
3.750 0.8575 0.00971 0.00389 -0.0659 0.3936 1.0000
4.000 0.8809 0.00988 0.00401 -0.0650 0.3819 1.0000
4.250 0.9041 0.01006 0.00414 -0.0641 0.3723 1.0000
4.500 0.9271 0.01026 0.00428 -0.0632 0.3641 1.0000
4.750 0.9501 0.01044 0.00443 -0.0623 0.3568 1.0000
5.000 0.9729 0.01063 0.00459 -0.0613 0.3489 1.0000
5.250 0.9952 0.01085 0.00477 -0.0603 0.3427 1.0000
5.500 1.0183 0.01101 0.00493 -0.0594 0.3366 1.0000
5.750 1.0402 0.01124 0.00512 -0.0583 0.3304 1.0000
6.000 1.0623 0.01144 0.00532 -0.0572 0.3255 1.0000
6.250 1.0849 0.01160 0.00550 -0.0562 0.3207 1.0000
6.500 1.1065 0.01182 0.00570 -0.0551 0.3158 1.0000
6.750 1.1268 0.01211 0.00596 -0.0538 0.3109 1.0000
7.000 1.1492 0.01225 0.00615 -0.0528 0.3069 1.0000
7.250 1.1704 0.01244 0.00636 -0.0516 0.3021 1.0000
7.500 1.1903 0.01270 0.00661 -0.0502 0.2974 1.0000
7.750 1.2100 0.01295 0.00687 -0.0487 0.2928 1.0000
8.000 1.2308 0.01312 0.00709 -0.0475 0.2880 1.0000
8.250 1.2499 0.01336 0.00734 -0.0459 0.2829 1.0000
8.500 1.2669 0.01369 0.00765 -0.0441 0.2776 1.0000
8.750 1.2867 0.01385 0.00788 -0.0427 0.2723 1.0000
9.000 1.3035 0.01412 0.00815 -0.0408 0.2657 1.0000
9.250 1.3196 0.01441 0.00846 -0.0387 0.2591 1.0000
9.500 1.3351 0.01468 0.00875 -0.0366 0.2509 1.0000
9.750 1.3483 0.01502 0.00908 -0.0342 0.2424 1.0000
10.000 1.3577 0.01545 0.00948 -0.0311 0.2313 1.0000
10.250 1.3652 0.01591 0.00991 -0.0278 0.2172 1.0000
10.500 1.3636 0.01643 0.01037 -0.0228 0.2036 1.0000
10.750 1.3600 0.01710 0.01099 -0.0178 0.1901 1.0000
11.000 1.3584 0.01797 0.01180 -0.0137 0.1781 1.0000
11.250 1.3592 0.01899 0.01279 -0.0105 0.1693 1.0000
11.500 1.3609 0.02018 0.01396 -0.0079 0.1617 1.0000
11.750 1.3658 0.02139 0.01518 -0.0060 0.1558 1.0000
12.000 1.3716 0.02264 0.01644 -0.0044 0.1510 1.0000
12.250 1.3745 0.02419 0.01798 -0.0028 0.1467 1.0000
12.500 1.3826 0.02543 0.01927 -0.0016 0.1433 1.0000
12.750 1.3904 0.02674 0.02062 -0.0005 0.1399 1.0000
13.000 1.3953 0.02832 0.02222 0.0006 0.1368 1.0000
13.250 1.3985 0.03006 0.02398 0.0017 0.1340 1.0000
13.500 1.4031 0.03173 0.02570 0.0027 0.1316 1.0000
13.750 1.4124 0.03305 0.02710 0.0034 0.1297 1.0000
14.000 1.4195 0.03458 0.02869 0.0041 0.1275 1.0000
14.250 1.4241 0.03636 0.03052 0.0047 0.1250 1.0000
14.500 1.4272 0.03827 0.03248 0.0054 0.1232 1.0000
14.750 1.4261 0.04060 0.03482 0.0061 0.1201 1.0000
15.000 1.4308 0.04246 0.03675 0.0066 0.1186 1.0000
15.250 1.4386 0.04415 0.03853 0.0068 0.1168 1.0000
15.500 1.4446 0.04603 0.04049 0.0071 0.1143 1.0000
15.750 1.4471 0.04831 0.04283 0.0072 0.1118 1.0000
16.000 1.4463 0.05098 0.04552 0.0072 0.1092 1.0000
16.250 1.4456 0.05364 0.04822 0.0073 0.1067 1.0000
16.500 1.4527 0.05561 0.05030 0.0072 0.1047 1.0000
16.750 1.4568 0.05792 0.05270 0.0070 0.1021 1.0000
17.000 1.4574 0.06065 0.05549 0.0068 0.0992 1.0000
17.250 1.4515 0.06418 0.05904 0.0063 0.0959 1.0000
17.500 1.4557 0.06659 0.06156 0.0059 0.0930 1.0000
17.750 1.4562 0.06949 0.06453 0.0054 0.0885 1.0000
18.000 1.4507 0.07319 0.06826 0.0047 0.0837 1.0000
18.250 1.4434 0.07719 0.07229 0.0037 0.0750 1.0000
18.500 1.4302 0.08203 0.07712 0.0025 0.0662 1.0000
18.750 1.4071 0.08831 0.08338 0.0007 0.0568 1.0000
19.000 1.3868 0.09430 0.08940 -0.0011 0.0507 1.0000
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