ULTIMATE (ultimate-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: ULTIMATE (ultimate-il) Reynolds number: 50,000 Max Cl/Cd: 27.54 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ultimate-il-50000-n5.txt Download as CSV file: xf-ultimate-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ULTIMATE
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7467 0.11642 0.10925 -0.0052 1.0000 0.0496
-13.000 -0.7642 0.10783 0.10066 -0.0103 1.0000 0.0493
-12.750 -0.7838 0.09958 0.09235 -0.0154 1.0000 0.0489
-12.500 -0.8063 0.09172 0.08439 -0.0203 1.0000 0.0485
-12.250 -0.8291 0.08474 0.07727 -0.0243 1.0000 0.0481
-12.000 -0.8520 0.07863 0.07098 -0.0272 1.0000 0.0479
-11.750 -0.8730 0.07344 0.06557 -0.0287 1.0000 0.0478
-11.500 -0.8924 0.06897 0.06085 -0.0289 1.0000 0.0479
-11.250 -0.9098 0.06511 0.05670 -0.0279 1.0000 0.0482
-11.000 -0.9243 0.06172 0.05299 -0.0258 1.0000 0.0486
-10.750 -0.9359 0.05872 0.04963 -0.0229 1.0000 0.0491
-10.500 -0.9394 0.05561 0.04621 -0.0205 1.0000 0.0499
-10.250 -0.9310 0.05258 0.04301 -0.0193 1.0000 0.0510
-9.750 -0.9086 0.04741 0.03738 -0.0166 1.0000 0.0540
-9.500 -0.8953 0.04516 0.03486 -0.0153 1.0000 0.0568
-9.250 -0.8792 0.04296 0.03226 -0.0140 1.0000 0.0600
-9.000 -0.8574 0.04072 0.02994 -0.0135 1.0000 0.0629
-8.750 -0.8374 0.03888 0.02803 -0.0126 1.0000 0.0664
-8.500 -0.8186 0.03725 0.02614 -0.0114 1.0000 0.0718
-8.250 -0.8026 0.03559 0.02449 -0.0101 1.0000 0.0771
-8.000 -0.7867 0.03407 0.02285 -0.0084 1.0000 0.0833
-7.750 -0.7739 0.03254 0.02132 -0.0066 1.0000 0.0914
-7.500 -0.7618 0.03104 0.01982 -0.0045 1.0000 0.1031
-7.250 -0.7509 0.02946 0.01834 -0.0023 1.0000 0.1199
-7.000 -0.7417 0.02776 0.01687 0.0000 1.0000 0.1529
-6.750 -0.7343 0.02610 0.01565 0.0027 1.0000 0.2103
-6.500 -0.7266 0.02490 0.01489 0.0057 1.0000 0.2820
-6.250 -0.7162 0.02418 0.01436 0.0086 1.0000 0.3437
-6.000 -0.7051 0.02365 0.01391 0.0116 1.0000 0.3944
-5.750 -0.6950 0.02322 0.01367 0.0151 1.0000 0.4449
-5.500 -0.6830 0.02290 0.01347 0.0184 1.0000 0.4892
-5.250 -0.6669 0.02262 0.01323 0.0210 1.0000 0.5227
-5.000 -0.6485 0.02233 0.01290 0.0230 1.0000 0.5495
-4.750 -0.6297 0.02206 0.01257 0.0250 1.0000 0.5749
-4.500 -0.6093 0.02186 0.01232 0.0267 1.0000 0.5988
-4.250 -0.5903 0.02165 0.01204 0.0285 1.0000 0.6235
-4.000 -0.5697 0.02150 0.01185 0.0302 1.0000 0.6475
-3.750 -0.5496 0.02136 0.01166 0.0319 1.0000 0.6719
-3.500 -0.5295 0.02123 0.01146 0.0335 1.0000 0.6966
-3.250 -0.5077 0.02116 0.01136 0.0349 1.0000 0.7202
-3.000 -0.4880 0.02107 0.01121 0.0365 1.0000 0.7450
-2.750 -0.4629 0.02108 0.01119 0.0373 1.0000 0.7674
-2.500 -0.4408 0.02105 0.01108 0.0383 1.0000 0.7915
-2.250 -0.4116 0.02115 0.01114 0.0382 1.0000 0.8131
-2.000 -0.3851 0.02123 0.01116 0.0382 1.0000 0.8364
-1.750 -0.3520 0.02139 0.01125 0.0370 1.0000 0.8575
-1.500 -0.3096 0.02160 0.01139 0.0337 0.9969 0.8776
-1.250 -0.2524 0.02186 0.01155 0.0275 0.9887 0.8947
-1.000 -0.1923 0.02211 0.01170 0.0206 0.9803 0.9087
-0.750 -0.1290 0.02233 0.01185 0.0131 0.9723 0.9201
-0.500 -0.0695 0.02248 0.01196 0.0063 0.9620 0.9312
-0.250 -0.0121 0.02255 0.01202 -0.0002 0.9507 0.9423
0.000 0.0466 0.02257 0.01205 -0.0068 0.9385 0.9516
0.250 0.1014 0.02252 0.01204 -0.0127 0.9250 0.9621
0.500 0.1537 0.02242 0.01200 -0.0180 0.9108 0.9731
0.750 0.2040 0.02231 0.01197 -0.0229 0.8960 0.9847
1.000 0.2537 0.02217 0.01190 -0.0277 0.8804 0.9959
1.250 0.2886 0.02200 0.01179 -0.0295 0.8622 1.0000
1.500 0.3113 0.02188 0.01171 -0.0289 0.8430 1.0000
1.750 0.3313 0.02182 0.01170 -0.0277 0.8231 1.0000
2.000 0.3506 0.02179 0.01172 -0.0264 0.8031 1.0000
2.250 0.3703 0.02176 0.01173 -0.0250 0.7845 1.0000
2.500 0.3901 0.02172 0.01176 -0.0235 0.7669 1.0000
2.750 0.4098 0.02171 0.01179 -0.0219 0.7496 1.0000
3.000 0.4291 0.02176 0.01190 -0.0203 0.7311 1.0000
3.250 0.4488 0.02181 0.01201 -0.0186 0.7128 1.0000
3.500 0.4688 0.02184 0.01212 -0.0169 0.6941 1.0000
3.750 0.4892 0.02188 0.01219 -0.0151 0.6754 1.0000
4.000 0.5098 0.02199 0.01237 -0.0134 0.6556 1.0000
4.250 0.5306 0.02215 0.01262 -0.0118 0.6352 1.0000
4.500 0.5520 0.02231 0.01290 -0.0103 0.6153 1.0000
4.750 0.5734 0.02250 0.01319 -0.0087 0.5947 1.0000
5.000 0.5933 0.02261 0.01337 -0.0067 0.5668 1.0000
5.250 0.6088 0.02258 0.01322 -0.0035 0.5170 1.0000
5.500 0.6223 0.02272 0.01314 -0.0003 0.4490 1.0000
5.750 0.6376 0.02315 0.01341 0.0021 0.3820 1.0000
6.000 0.6500 0.02402 0.01383 0.0046 0.2817 1.0000
6.250 0.6574 0.02591 0.01489 0.0070 0.1731 1.0000
6.500 0.6673 0.02783 0.01636 0.0091 0.1217 1.0000
6.750 0.6790 0.02945 0.01780 0.0111 0.1014 1.0000
7.000 0.6914 0.03093 0.01920 0.0131 0.0896 1.0000
7.250 0.7057 0.03228 0.02067 0.0150 0.0821 1.0000
7.500 0.7194 0.03376 0.02212 0.0169 0.0760 1.0000
7.750 0.7363 0.03510 0.02362 0.0186 0.0699 1.0000
8.000 0.7541 0.03665 0.02516 0.0200 0.0661 1.0000
8.250 0.7761 0.03839 0.02704 0.0211 0.0630 1.0000
8.500 0.7969 0.04012 0.02903 0.0223 0.0592 1.0000
8.750 0.8153 0.04195 0.03100 0.0234 0.0558 1.0000
9.000 0.8348 0.04417 0.03330 0.0243 0.0538 1.0000
9.250 0.8529 0.04692 0.03623 0.0253 0.0525 1.0000
9.500 0.8631 0.04954 0.03934 0.0271 0.0512 1.0000
9.750 0.8689 0.05234 0.04256 0.0292 0.0497 1.0000
10.000 0.8709 0.05523 0.04582 0.0313 0.0483 1.0000
10.250 0.8693 0.05823 0.04912 0.0334 0.0472 1.0000
10.500 0.8636 0.06137 0.05254 0.0356 0.0465 1.0000
10.750 0.8516 0.06465 0.05606 0.0380 0.0462 1.0000
11.000 0.8340 0.06818 0.05980 0.0400 0.0462 1.0000
11.250 0.8132 0.07239 0.06422 0.0406 0.0463 1.0000
11.500 0.7892 0.07757 0.06960 0.0396 0.0466 1.0000
11.750 0.7620 0.08407 0.07625 0.0366 0.0471 1.0000
12.000 0.7324 0.09225 0.08455 0.0317 0.0478 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ULTIMATE (ultimate-il)