S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 200,000 Max Cl/Cd: 55.99 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1048-il-200000.txt Download as CSV file: xf-s1048-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S1048 14% (Danny Howell)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8646 0.11654 0.11252 -0.0050 1.0000 0.0223
-16.000 -0.8834 0.10817 0.10398 -0.0109 1.0000 0.0221
-15.750 -0.9013 0.10056 0.09621 -0.0154 1.0000 0.0219
-15.500 -0.9219 0.09294 0.08841 -0.0201 1.0000 0.0218
-15.250 -0.9403 0.08607 0.08137 -0.0240 1.0000 0.0217
-15.000 -0.9569 0.07996 0.07507 -0.0274 1.0000 0.0217
-14.750 -0.9710 0.07445 0.06938 -0.0300 1.0000 0.0215
-14.500 -0.9877 0.06917 0.06388 -0.0328 1.0000 0.0218
-14.250 -0.9989 0.06470 0.05920 -0.0347 1.0000 0.0218
-14.000 -1.0092 0.06064 0.05494 -0.0361 1.0000 0.0219
-13.750 -1.0206 0.05644 0.05052 -0.0371 1.0000 0.0222
-13.500 -1.0221 0.05256 0.04649 -0.0371 1.0000 0.0228
-13.250 -1.0200 0.04967 0.04348 -0.0370 1.0000 0.0230
-13.000 -1.0170 0.04727 0.04105 -0.0370 1.0000 0.0240
-12.750 -1.0137 0.04487 0.03853 -0.0367 1.0000 0.0245
-12.500 -1.0085 0.04256 0.03609 -0.0362 1.0000 0.0250
-12.250 -1.0022 0.04038 0.03377 -0.0355 1.0000 0.0258
-12.000 -0.9942 0.03836 0.03162 -0.0346 1.0000 0.0265
-11.750 -0.9860 0.03649 0.02960 -0.0337 1.0000 0.0274
-11.500 -0.9777 0.03483 0.02777 -0.0327 1.0000 0.0283
-11.250 -0.9737 0.03240 0.02539 -0.0312 1.0000 0.0299
-11.000 -0.9687 0.03078 0.02376 -0.0300 1.0000 0.0317
-10.750 -0.9627 0.02930 0.02220 -0.0285 1.0000 0.0337
-10.500 -0.9550 0.02802 0.02079 -0.0267 1.0000 0.0356
-10.250 -0.9580 0.02613 0.01894 -0.0238 1.0000 0.0382
-10.000 -0.9549 0.02490 0.01768 -0.0210 1.0000 0.0412
-9.750 -0.9488 0.02379 0.01647 -0.0182 1.0000 0.0454
-9.500 -0.9454 0.02235 0.01508 -0.0153 1.0000 0.0520
-9.250 -0.9387 0.02101 0.01376 -0.0127 1.0000 0.0623
-9.000 -0.9316 0.01960 0.01247 -0.0100 1.0000 0.0824
-8.750 -0.9222 0.01833 0.01141 -0.0077 1.0000 0.1126
-8.500 -0.9085 0.01740 0.01062 -0.0059 1.0000 0.1439
-8.250 -0.8928 0.01666 0.00999 -0.0042 1.0000 0.1724
-8.000 -0.8761 0.01603 0.00945 -0.0026 1.0000 0.1980
-7.750 -0.8585 0.01551 0.00898 -0.0011 1.0000 0.2221
-7.500 -0.8398 0.01509 0.00857 0.0004 1.0000 0.2454
-7.250 -0.8220 0.01468 0.00824 0.0019 1.0000 0.2674
-7.000 -0.8031 0.01438 0.00794 0.0034 1.0000 0.2902
-6.750 -0.7850 0.01408 0.00769 0.0050 1.0000 0.3099
-6.500 -0.7665 0.01382 0.00743 0.0066 1.0000 0.3272
-6.250 -0.7487 0.01359 0.00720 0.0083 1.0000 0.3432
-6.000 -0.7320 0.01339 0.00701 0.0101 1.0000 0.3585
-5.750 -0.7167 0.01324 0.00687 0.0121 1.0000 0.3731
-5.500 -0.6994 0.01312 0.00675 0.0136 0.9993 0.3875
-5.250 -0.6541 0.01300 0.00657 0.0097 0.9909 0.4074
-5.000 -0.6089 0.01284 0.00642 0.0060 0.9827 0.4252
-4.750 -0.5669 0.01265 0.00624 0.0029 0.9726 0.4418
-4.500 -0.5244 0.01246 0.00606 -0.0001 0.9631 0.4581
-4.250 -0.4799 0.01227 0.00587 -0.0034 0.9553 0.4742
-4.000 -0.4414 0.01208 0.00567 -0.0055 0.9428 0.4891
-3.750 -0.4043 0.01190 0.00549 -0.0072 0.9295 0.5035
-3.500 -0.3700 0.01175 0.00533 -0.0083 0.9147 0.5174
-3.250 -0.3391 0.01163 0.00517 -0.0086 0.8987 0.5311
-3.000 -0.3111 0.01154 0.00504 -0.0082 0.8820 0.5446
-2.750 -0.2846 0.01147 0.00495 -0.0076 0.8653 0.5571
-2.500 -0.2588 0.01140 0.00486 -0.0068 0.8491 0.5695
-2.250 -0.2333 0.01135 0.00479 -0.0060 0.8327 0.5820
-2.000 -0.2077 0.01132 0.00472 -0.0052 0.8167 0.5948
-1.750 -0.1821 0.01129 0.00465 -0.0045 0.8013 0.6079
-1.500 -0.1563 0.01127 0.00459 -0.0038 0.7864 0.6213
-1.250 -0.1305 0.01126 0.00454 -0.0031 0.7717 0.6346
-1.000 -0.1044 0.01124 0.00452 -0.0024 0.7575 0.6473
-0.750 -0.0784 0.01122 0.00450 -0.0018 0.7429 0.6602
-0.500 -0.0523 0.01121 0.00449 -0.0012 0.7286 0.6734
-0.250 -0.0262 0.01120 0.00447 -0.0006 0.7144 0.6868
0.000 0.0000 0.01120 0.00447 0.0000 0.7006 0.7006
0.250 0.0261 0.01120 0.00447 0.0006 0.6868 0.7144
0.500 0.0523 0.01121 0.00449 0.0012 0.6734 0.7286
0.750 0.0784 0.01122 0.00450 0.0018 0.6602 0.7429
1.000 0.1044 0.01124 0.00452 0.0024 0.6473 0.7575
1.250 0.1304 0.01126 0.00454 0.0031 0.6345 0.7717
1.500 0.1563 0.01127 0.00459 0.0038 0.6213 0.7864
1.750 0.1821 0.01129 0.00464 0.0045 0.6079 0.8013
2.000 0.2077 0.01131 0.00472 0.0052 0.5948 0.8167
2.250 0.2333 0.01135 0.00479 0.0060 0.5820 0.8327
2.500 0.2588 0.01140 0.00486 0.0068 0.5696 0.8491
2.750 0.2846 0.01147 0.00495 0.0076 0.5571 0.8653
3.000 0.3111 0.01154 0.00504 0.0082 0.5446 0.8820
3.250 0.3391 0.01163 0.00517 0.0086 0.5311 0.8987
3.500 0.3700 0.01175 0.00533 0.0083 0.5174 0.9147
3.750 0.4043 0.01190 0.00549 0.0072 0.5035 0.9295
4.000 0.4414 0.01208 0.00567 0.0055 0.4891 0.9428
4.250 0.4800 0.01227 0.00587 0.0034 0.4741 0.9553
4.500 0.5244 0.01246 0.00606 0.0001 0.4581 0.9631
4.750 0.5668 0.01265 0.00624 -0.0029 0.4418 0.9726
5.000 0.6090 0.01284 0.00642 -0.0060 0.4253 0.9827
5.250 0.6542 0.01300 0.00657 -0.0097 0.4075 0.9909
5.500 0.6995 0.01312 0.00675 -0.0136 0.3876 0.9993
5.750 0.7167 0.01324 0.00686 -0.0121 0.3730 1.0000
6.000 0.7320 0.01339 0.00701 -0.0101 0.3585 1.0000
6.250 0.7487 0.01359 0.00720 -0.0083 0.3433 1.0000
6.500 0.7665 0.01382 0.00743 -0.0066 0.3273 1.0000
6.750 0.7850 0.01408 0.00769 -0.0050 0.3099 1.0000
7.000 0.8032 0.01438 0.00794 -0.0034 0.2903 1.0000
7.250 0.8220 0.01468 0.00823 -0.0019 0.2673 1.0000
7.500 0.8399 0.01509 0.00857 -0.0004 0.2453 1.0000
7.750 0.8585 0.01551 0.00898 0.0011 0.2221 1.0000
8.000 0.8761 0.01603 0.00945 0.0026 0.1980 1.0000
8.250 0.8928 0.01666 0.00999 0.0042 0.1724 1.0000
8.500 0.9085 0.01740 0.01062 0.0059 0.1439 1.0000
8.750 0.9222 0.01833 0.01141 0.0077 0.1123 1.0000
9.000 0.9317 0.01959 0.01246 0.0100 0.0824 1.0000
9.250 0.9388 0.02100 0.01375 0.0127 0.0625 1.0000
9.500 0.9453 0.02235 0.01508 0.0153 0.0519 1.0000
9.750 0.9493 0.02376 0.01645 0.0181 0.0456 1.0000
10.000 0.9551 0.02489 0.01767 0.0210 0.0415 1.0000
10.250 0.9584 0.02611 0.01892 0.0238 0.0382 1.0000
10.500 0.9553 0.02800 0.02078 0.0267 0.0356 1.0000
10.750 0.9633 0.02922 0.02213 0.0284 0.0332 1.0000
11.000 0.9691 0.03071 0.02368 0.0298 0.0313 1.0000
11.250 0.9735 0.03242 0.02540 0.0311 0.0297 1.0000
11.500 0.9783 0.03480 0.02776 0.0327 0.0283 1.0000
11.750 0.9866 0.03648 0.02958 0.0336 0.0274 1.0000
12.000 0.9951 0.03838 0.03164 0.0346 0.0266 1.0000
12.250 1.0030 0.04036 0.03375 0.0354 0.0259 1.0000
12.500 1.0096 0.04251 0.03603 0.0361 0.0252 1.0000
12.750 1.0146 0.04484 0.03850 0.0367 0.0246 1.0000
13.000 1.0177 0.04725 0.04103 0.0369 0.0239 1.0000
13.250 1.0202 0.04978 0.04365 0.0370 0.0234 1.0000
13.500 1.0239 0.05309 0.04697 0.0373 0.0221 1.0000
13.750 1.0213 0.05646 0.05054 0.0371 0.0222 1.0000
14.000 1.0118 0.06055 0.05483 0.0362 0.0220 1.0000
14.250 1.0002 0.06461 0.05911 0.0346 0.0218 1.0000
14.500 0.9878 0.06930 0.06402 0.0327 0.0217 1.0000
14.750 0.9748 0.07430 0.06920 0.0304 0.0218 1.0000
15.000 0.9581 0.07991 0.07503 0.0272 0.0217 1.0000
15.250 0.9412 0.08607 0.08137 0.0238 0.0217 1.0000
15.500 0.9229 0.09293 0.08841 0.0199 0.0218 1.0000
15.750 0.9029 0.10047 0.09611 0.0154 0.0219 1.0000
16.000 0.8851 0.10805 0.10385 0.0108 0.0221 1.0000
16.250 0.8649 0.11668 0.11266 0.0048 0.0223 1.0000
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Polar data table (+)
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