RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.22 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf33-il-1000000.txt Download as CSV file: xf-raf33-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 33 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3065 0.08190 0.07900 -0.0438 0.6434 0.0255
-9.250 -0.3136 0.07755 0.07466 -0.0460 0.6396 0.0256
-9.000 -0.3428 0.07145 0.06858 -0.0487 0.6365 0.0259
-8.750 -0.3475 0.06916 0.06627 -0.0482 0.6324 0.0260
-8.500 -0.3528 0.06703 0.06414 -0.0468 0.6290 0.0262
-8.250 -0.3532 0.06480 0.06190 -0.0462 0.6252 0.0264
-8.000 -0.3537 0.06186 0.05890 -0.0460 0.6215 0.0265
-7.750 -0.5176 0.02513 0.02053 -0.0352 0.6258 0.0260
-7.500 -0.5027 0.02344 0.01864 -0.0333 0.6218 0.0263
-7.250 -0.4810 0.02288 0.01800 -0.0324 0.6173 0.0266
-7.000 -0.4611 0.02182 0.01680 -0.0311 0.6138 0.0269
-6.750 -0.4385 0.02119 0.01610 -0.0302 0.6101 0.0272
-6.500 -0.4149 0.02077 0.01562 -0.0295 0.6063 0.0276
-6.250 -0.3942 0.01969 0.01433 -0.0282 0.6025 0.0280
-6.000 -0.3742 0.01823 0.01262 -0.0267 0.5989 0.0283
-5.750 -0.3519 0.01700 0.01120 -0.0256 0.5956 0.0286
-5.500 -0.3281 0.01608 0.01011 -0.0247 0.5921 0.0290
-5.250 -0.3035 0.01534 0.00921 -0.0240 0.5886 0.0294
-5.000 -0.2782 0.01481 0.00854 -0.0233 0.5846 0.0297
-4.750 -0.2519 0.01442 0.00807 -0.0229 0.5814 0.0300
-4.500 -0.2256 0.01403 0.00760 -0.0224 0.5781 0.0303
-4.250 -0.2001 0.01275 0.00619 -0.0220 0.5748 0.0310
-4.000 -0.1737 0.01224 0.00563 -0.0216 0.5712 0.0314
-3.750 -0.1474 0.01189 0.00523 -0.0212 0.5672 0.0318
-3.500 -0.1204 0.01156 0.00489 -0.0209 0.5644 0.0323
-3.250 -0.0935 0.01125 0.00456 -0.0206 0.5611 0.0328
-3.000 -0.0668 0.01096 0.00424 -0.0202 0.5576 0.0333
-2.750 -0.0403 0.01073 0.00396 -0.0198 0.5539 0.0339
-2.500 -0.0138 0.01050 0.00370 -0.0194 0.5504 0.0344
-2.250 0.0133 0.01031 0.00350 -0.0191 0.5474 0.0352
-2.000 0.0406 0.01018 0.00336 -0.0188 0.5439 0.0357
-1.750 0.0657 0.00977 0.00291 -0.0181 0.5404 0.0368
-1.500 0.0916 0.00959 0.00270 -0.0176 0.5367 0.0378
-1.250 0.1182 0.00944 0.00256 -0.0173 0.5335 0.0388
-1.000 0.1451 0.00930 0.00243 -0.0169 0.5302 0.0401
-0.750 0.1720 0.00919 0.00231 -0.0166 0.5266 0.0414
-0.500 0.1983 0.00907 0.00216 -0.0162 0.5230 0.0430
-0.250 0.2243 0.00897 0.00205 -0.0157 0.5191 0.0461
0.000 0.2514 0.00888 0.00198 -0.0154 0.5161 0.0493
0.250 0.2778 0.00874 0.00188 -0.0150 0.5125 0.0563
0.500 0.3040 0.00864 0.00181 -0.0146 0.5087 0.0690
0.750 0.3295 0.00853 0.00179 -0.0141 0.5047 0.0995
1.000 0.3552 0.00840 0.00178 -0.0136 0.5012 0.1373
1.250 0.3799 0.00818 0.00178 -0.0130 0.4974 0.2108
1.500 0.4035 0.00796 0.00179 -0.0122 0.4930 0.3053
1.750 0.3925 0.00638 0.00169 -0.0041 0.4897 0.8043
2.000 0.4983 0.00642 0.00210 -0.0210 0.4825 0.9477
2.250 0.5242 0.00663 0.00227 -0.0203 0.4780 0.9589
2.500 0.5727 0.00697 0.00255 -0.0246 0.4725 0.9641
2.750 0.6036 0.00720 0.00277 -0.0250 0.4686 0.9716
3.000 0.6532 0.00740 0.00294 -0.0296 0.4632 0.9734
3.250 0.6954 0.00759 0.00307 -0.0328 0.4577 0.9756
3.500 0.7367 0.00774 0.00321 -0.0356 0.4529 0.9787
3.750 0.7635 0.00791 0.00337 -0.0354 0.4482 0.9827
4.000 0.7979 0.00799 0.00340 -0.0369 0.4420 0.9838
4.250 0.8355 0.00801 0.00343 -0.0391 0.4371 0.9848
4.500 0.8707 0.00806 0.00346 -0.0409 0.4311 0.9859
4.750 0.9013 0.00813 0.00350 -0.0416 0.4236 0.9868
5.000 0.9312 0.00819 0.00355 -0.0423 0.4157 0.9878
5.250 0.9604 0.00828 0.00361 -0.0428 0.4085 0.9889
5.500 0.9896 0.00835 0.00368 -0.0433 0.4012 0.9900
5.750 1.0179 0.00848 0.00379 -0.0436 0.3940 0.9914
6.000 1.0462 0.00860 0.00390 -0.0439 0.3857 0.9929
6.250 1.0748 0.00874 0.00402 -0.0444 0.3769 0.9940
6.500 1.1056 0.00884 0.00411 -0.0453 0.3675 0.9948
6.750 1.1358 0.00898 0.00421 -0.0462 0.3561 0.9956
7.000 1.1653 0.00916 0.00436 -0.0469 0.3429 0.9966
7.250 1.1942 0.00941 0.00454 -0.0476 0.3267 0.9978
7.500 1.2232 0.00966 0.00474 -0.0484 0.3117 0.9989
7.750 1.2523 0.00993 0.00496 -0.0492 0.2974 0.9998
8.000 1.2747 0.01024 0.00523 -0.0486 0.2840 1.0000
8.250 1.2941 0.01061 0.00553 -0.0474 0.2685 1.0000
8.500 1.3124 0.01105 0.00589 -0.0460 0.2510 1.0000
8.750 1.3302 0.01149 0.00626 -0.0446 0.2353 1.0000
9.000 1.3473 0.01196 0.00667 -0.0432 0.2203 1.0000
9.250 1.3636 0.01246 0.00711 -0.0415 0.2057 1.0000
9.500 1.3780 0.01304 0.00761 -0.0397 0.1894 1.0000
9.750 1.3895 0.01375 0.00821 -0.0374 0.1701 1.0000
10.000 1.3959 0.01466 0.00899 -0.0344 0.1452 1.0000
10.250 1.3784 0.01651 0.01055 -0.0281 0.0953 1.0000
10.750 1.3498 0.01903 0.01306 -0.0170 0.0780 1.0000
11.000 1.3473 0.02048 0.01452 -0.0142 0.0715 1.0000
11.250 1.3493 0.02185 0.01592 -0.0121 0.0660 1.0000
11.500 1.3498 0.02344 0.01752 -0.0101 0.0596 1.0000
11.750 1.3480 0.02533 0.01938 -0.0082 0.0501 1.0000
12.000 1.3397 0.02783 0.02179 -0.0063 0.0356 1.0000
12.250 1.3346 0.03019 0.02412 -0.0047 0.0271 1.0000
12.500 1.3308 0.03253 0.02647 -0.0033 0.0225 1.0000
12.750 1.3296 0.03471 0.02868 -0.0021 0.0202 1.0000
13.000 1.3312 0.03669 0.03071 -0.0012 0.0191 1.0000
13.250 1.3295 0.03902 0.03308 -0.0002 0.0179 1.0000
13.500 1.3280 0.04141 0.03552 0.0006 0.0171 1.0000
13.750 1.3303 0.04353 0.03771 0.0012 0.0166 1.0000
14.000 1.3318 0.04581 0.04005 0.0017 0.0161 1.0000
14.250 1.3317 0.04829 0.04260 0.0021 0.0157 1.0000
14.500 1.3310 0.05092 0.04528 0.0025 0.0151 1.0000
14.750 1.3286 0.05379 0.04821 0.0027 0.0148 1.0000
15.000 1.3256 0.05679 0.05128 0.0028 0.0144 1.0000
15.250 1.3170 0.06055 0.05512 0.0029 0.0139 1.0000
15.500 1.3177 0.06323 0.05787 0.0028 0.0137 1.0000
15.750 1.3163 0.06622 0.06093 0.0028 0.0134 1.0000
16.000 1.3164 0.06907 0.06384 0.0026 0.0131 1.0000
16.250 1.3124 0.07248 0.06733 0.0023 0.0130 1.0000
16.500 1.3105 0.07566 0.07058 0.0020 0.0126 1.0000
16.750 1.3071 0.07909 0.07408 0.0016 0.0125 1.0000
17.000 1.3020 0.08276 0.07781 0.0011 0.0120 1.0000
17.250 1.2974 0.08645 0.08156 0.0005 0.0119 1.0000
17.500 1.2907 0.09048 0.08567 -0.0003 0.0117 1.0000
17.750 1.2823 0.09479 0.09005 -0.0011 0.0115 1.0000
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Polar data table (+)
Polar graphs
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