BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 200,000 Max Cl/Cd: 57.68 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v23010-il-200000-n5.txt Download as CSV file: xf-v23010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5248 0.10879 0.10486 -0.0050 1.0000 0.0372
-10.250 -0.5315 0.10320 0.09930 -0.0098 1.0000 0.0375
-10.000 -0.5391 0.09707 0.09320 -0.0152 1.0000 0.0376
-9.750 -0.5356 0.09311 0.08927 -0.0156 1.0000 0.0378
-9.500 -0.5250 0.09117 0.08735 -0.0137 1.0000 0.0382
-9.250 -0.5192 0.08837 0.08458 -0.0137 1.0000 0.0388
-9.000 -0.5184 0.08460 0.08083 -0.0156 1.0000 0.0392
-8.750 -0.5230 0.07975 0.07602 -0.0191 1.0000 0.0395
-8.500 -0.5365 0.07415 0.07043 -0.0241 1.0000 0.0396
-8.250 -0.5486 0.07031 0.06655 -0.0249 1.0000 0.0399
-8.000 -0.5545 0.06645 0.06262 -0.0256 1.0000 0.0403
-7.750 -0.5570 0.06280 0.05887 -0.0258 1.0000 0.0408
-7.500 -0.5568 0.05927 0.05521 -0.0256 1.0000 0.0415
-7.250 -0.5541 0.05589 0.05165 -0.0249 1.0000 0.0423
-7.000 -0.5577 0.05335 0.04842 -0.0226 1.0000 0.0440
-6.750 -0.5568 0.04460 0.03924 -0.0203 1.0000 0.0321
-6.500 -0.5425 0.04231 0.03695 -0.0193 1.0000 0.0318
-6.250 -0.5310 0.03975 0.03416 -0.0174 1.0000 0.0318
-6.000 -0.5184 0.03734 0.03152 -0.0154 1.0000 0.0318
-5.750 -0.5042 0.03522 0.02930 -0.0138 1.0000 0.0316
-5.500 -0.4898 0.03323 0.02719 -0.0120 1.0000 0.0313
-5.250 -0.4752 0.03132 0.02511 -0.0101 1.0000 0.0309
-5.000 -0.4586 0.02940 0.02300 -0.0084 0.9994 0.0306
-4.750 -0.4235 0.02705 0.02035 -0.0102 0.9916 0.0303
-4.500 -0.3866 0.02492 0.01794 -0.0122 0.9829 0.0301
-4.250 -0.3493 0.02306 0.01579 -0.0140 0.9724 0.0301
-4.000 -0.3123 0.02150 0.01400 -0.0157 0.9589 0.0306
-3.750 -0.2760 0.02020 0.01246 -0.0171 0.9402 0.0313
-3.500 -0.2394 0.01896 0.01103 -0.0185 0.9173 0.0316
-3.250 -0.2034 0.01785 0.00977 -0.0198 0.8931 0.0316
-3.000 -0.1702 0.01692 0.00870 -0.0204 0.8676 0.0318
-2.750 -0.1412 0.01618 0.00784 -0.0202 0.8423 0.0320
-2.500 -0.1149 0.01547 0.00707 -0.0196 0.8153 0.0323
-2.250 -0.0896 0.01491 0.00645 -0.0188 0.7881 0.0328
-2.000 -0.0648 0.01446 0.00591 -0.0178 0.7651 0.0333
-1.750 -0.0403 0.01408 0.00545 -0.0169 0.7438 0.0339
-1.500 -0.0157 0.01378 0.00508 -0.0160 0.7224 0.0351
-1.250 0.0089 0.01352 0.00474 -0.0151 0.6987 0.0367
-1.000 0.0333 0.01326 0.00438 -0.0142 0.6706 0.0377
-0.750 0.0570 0.01298 0.00401 -0.0132 0.6371 0.0387
-0.500 0.0811 0.01283 0.00371 -0.0122 0.6007 0.0400
-0.250 0.1054 0.01276 0.00345 -0.0113 0.5639 0.0418
0.000 0.1299 0.01275 0.00323 -0.0104 0.5250 0.0440
0.250 0.1542 0.01275 0.00305 -0.0096 0.4821 0.0479
0.500 0.1785 0.01279 0.00290 -0.0087 0.4391 0.0576
0.750 0.1934 0.01139 0.00269 -0.0069 0.4079 0.4598
1.000 0.2067 0.01061 0.00283 -0.0037 0.3826 0.7257
1.250 0.2319 0.01053 0.00301 -0.0023 0.3583 0.8482
1.500 0.2926 0.01082 0.00330 -0.0081 0.3324 0.9499
1.750 0.3380 0.01110 0.00342 -0.0116 0.3162 0.9731
2.000 0.3760 0.01131 0.00349 -0.0137 0.3034 0.9827
2.250 0.4137 0.01149 0.00355 -0.0158 0.2917 0.9900
2.500 0.4507 0.01168 0.00362 -0.0179 0.2811 0.9971
2.750 0.4797 0.01186 0.00371 -0.0183 0.2727 1.0000
3.000 0.5017 0.01204 0.00381 -0.0172 0.2665 1.0000
3.250 0.5241 0.01220 0.00394 -0.0161 0.2612 1.0000
3.500 0.5466 0.01241 0.00409 -0.0151 0.2565 1.0000
3.750 0.5691 0.01264 0.00426 -0.0141 0.2523 1.0000
4.000 0.5925 0.01282 0.00445 -0.0132 0.2479 1.0000
4.250 0.6158 0.01302 0.00465 -0.0123 0.2433 1.0000
4.500 0.6389 0.01327 0.00485 -0.0113 0.2388 1.0000
4.750 0.6622 0.01352 0.00508 -0.0105 0.2343 1.0000
5.000 0.6861 0.01371 0.00531 -0.0096 0.2291 1.0000
5.250 0.7096 0.01395 0.00554 -0.0088 0.2240 1.0000
5.500 0.7327 0.01425 0.00579 -0.0079 0.2196 1.0000
5.750 0.7569 0.01445 0.00607 -0.0072 0.2146 1.0000
6.000 0.7807 0.01468 0.00634 -0.0064 0.2093 1.0000
6.250 0.8040 0.01499 0.00661 -0.0055 0.2045 1.0000
6.500 0.8281 0.01523 0.00693 -0.0048 0.1991 1.0000
6.750 0.8519 0.01548 0.00724 -0.0041 0.1931 1.0000
7.000 0.8752 0.01579 0.00753 -0.0033 0.1876 1.0000
7.250 0.8993 0.01605 0.00789 -0.0026 0.1809 1.0000
7.500 0.9225 0.01635 0.00820 -0.0018 0.1749 1.0000
7.750 0.9463 0.01663 0.00855 -0.0011 0.1672 1.0000
8.000 0.9693 0.01692 0.00883 -0.0004 0.1590 1.0000
8.250 0.9925 0.01723 0.00916 0.0003 0.1496 1.0000
8.500 1.0151 0.01760 0.00956 0.0011 0.1416 1.0000
8.750 1.0371 0.01803 0.00999 0.0019 0.1348 1.0000
9.000 1.0593 0.01847 0.01049 0.0027 0.1295 1.0000
9.250 1.0810 0.01895 0.01102 0.0035 0.1236 1.0000
9.500 1.1018 0.01948 0.01158 0.0044 0.1180 1.0000
9.750 1.1231 0.01998 0.01217 0.0053 0.1118 1.0000
10.000 1.1427 0.02059 0.01281 0.0063 0.1057 1.0000
10.250 1.1636 0.02111 0.01345 0.0071 0.0986 1.0000
10.500 1.1830 0.02172 0.01413 0.0081 0.0904 1.0000
10.750 1.2018 0.02238 0.01483 0.0092 0.0793 1.0000
11.000 1.2181 0.02321 0.01566 0.0104 0.0667 1.0000
11.250 1.2317 0.02425 0.01667 0.0119 0.0573 1.0000
11.500 1.2433 0.02536 0.01781 0.0136 0.0512 1.0000
11.750 1.2525 0.02657 0.01905 0.0156 0.0470 1.0000
12.000 1.2599 0.02772 0.02030 0.0178 0.0442 1.0000
12.250 1.2641 0.02892 0.02160 0.0203 0.0419 1.0000
12.500 1.2649 0.03038 0.02314 0.0227 0.0401 1.0000
12.750 1.2630 0.03214 0.02498 0.0248 0.0387 1.0000
13.000 1.2638 0.03390 0.02689 0.0262 0.0375 1.0000
13.250 1.2622 0.03605 0.02919 0.0271 0.0363 1.0000
13.500 1.2581 0.03871 0.03198 0.0273 0.0354 1.0000
13.750 1.2518 0.04191 0.03532 0.0268 0.0346 1.0000
14.000 1.2426 0.04581 0.03935 0.0255 0.0339 1.0000
14.250 1.2304 0.05052 0.04420 0.0234 0.0335 1.0000
14.500 1.2168 0.05582 0.04962 0.0207 0.0331 1.0000
14.750 1.2011 0.06167 0.05560 0.0176 0.0328 1.0000
15.000 1.1867 0.06755 0.06161 0.0145 0.0323 1.0000
15.250 1.1729 0.07336 0.06757 0.0115 0.0320 1.0000
15.500 1.1588 0.07924 0.07357 0.0086 0.0316 1.0000
15.750 1.1455 0.08503 0.07948 0.0057 0.0312 1.0000
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Polar data table (+)
Polar graphs
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