ULTIMATE (ultimate-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ULTIMATE (ultimate-il) Reynolds number: 200,000 Max Cl/Cd: 41.95 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ultimate-il-200000-n5.txt Download as CSV file: xf-ultimate-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9695 0.08782 0.08343 -0.0102 1.0000 0.0143
-14.250 -1.0060 0.07433 0.06955 -0.0180 1.0000 0.0144
-14.000 -1.0207 0.06876 0.06380 -0.0206 1.0000 0.0145
-13.750 -1.0315 0.06409 0.05898 -0.0225 1.0000 0.0146
-13.500 -1.0415 0.05975 0.05445 -0.0239 1.0000 0.0147
-13.250 -1.0467 0.05632 0.05090 -0.0246 1.0000 0.0149
-13.000 -1.0512 0.05319 0.04762 -0.0250 1.0000 0.0152
-12.750 -1.0552 0.05021 0.04448 -0.0249 1.0000 0.0154
-12.500 -1.0577 0.04758 0.04168 -0.0244 1.0000 0.0157
-12.250 -1.0591 0.04511 0.03902 -0.0234 1.0000 0.0160
-12.000 -1.0592 0.04281 0.03652 -0.0221 1.0000 0.0163
-11.750 -1.0576 0.04061 0.03411 -0.0205 1.0000 0.0166
-11.500 -1.0536 0.03854 0.03182 -0.0186 1.0000 0.0170
-11.250 -1.0474 0.03662 0.02969 -0.0167 1.0000 0.0174
-11.000 -1.0391 0.03487 0.02773 -0.0149 1.0000 0.0178
-10.750 -1.0289 0.03325 0.02589 -0.0130 1.0000 0.0182
-10.500 -1.0172 0.03183 0.02427 -0.0112 1.0000 0.0187
-10.250 -1.0065 0.03020 0.02257 -0.0093 1.0000 0.0192
-10.000 -0.9951 0.02901 0.02133 -0.0073 1.0000 0.0198
-9.750 -0.9820 0.02805 0.02031 -0.0056 1.0000 0.0207
-9.500 -0.9667 0.02708 0.01926 -0.0040 1.0000 0.0217
-9.250 -0.9507 0.02605 0.01812 -0.0025 1.0000 0.0228
-9.000 -0.9342 0.02506 0.01698 -0.0010 1.0000 0.0237
-8.750 -0.9191 0.02396 0.01580 0.0007 1.0000 0.0246
-8.500 -0.9047 0.02288 0.01469 0.0025 1.0000 0.0257
-8.250 -0.8877 0.02205 0.01382 0.0040 1.0000 0.0270
-8.000 -0.8696 0.02132 0.01302 0.0054 1.0000 0.0289
-7.750 -0.8507 0.02067 0.01225 0.0068 1.0000 0.0308
-7.500 -0.8352 0.01977 0.01134 0.0086 1.0000 0.0329
-7.250 -0.8177 0.01910 0.01062 0.0102 1.0000 0.0353
-7.000 -0.7995 0.01855 0.00999 0.0118 1.0000 0.0385
-6.750 -0.7837 0.01792 0.00934 0.0138 1.0000 0.0423
-6.500 -0.7684 0.01740 0.00878 0.0160 1.0000 0.0472
-6.250 -0.7543 0.01689 0.00826 0.0184 1.0000 0.0537
-6.000 -0.7384 0.01633 0.00776 0.0204 0.9991 0.0668
-5.750 -0.7092 0.01542 0.00710 0.0193 0.9947 0.1109
-5.500 -0.6807 0.01453 0.00652 0.0184 0.9896 0.1744
-5.250 -0.6509 0.01377 0.00606 0.0173 0.9847 0.2388
-5.000 -0.6234 0.01320 0.00575 0.0168 0.9773 0.2987
-4.750 -0.5937 0.01281 0.00550 0.0161 0.9704 0.3441
-4.500 -0.5662 0.01246 0.00527 0.0160 0.9617 0.3864
-4.250 -0.5417 0.01211 0.00507 0.0166 0.9517 0.4292
-4.000 -0.5157 0.01182 0.00487 0.0169 0.9427 0.4600
-3.750 -0.4895 0.01159 0.00466 0.0173 0.9334 0.4808
-3.500 -0.4640 0.01137 0.00447 0.0179 0.9239 0.5015
-3.250 -0.4385 0.01115 0.00430 0.0185 0.9155 0.5235
-2.750 -0.3898 0.01077 0.00402 0.0204 0.8967 0.5734
-2.500 -0.3660 0.01060 0.00391 0.0215 0.8878 0.6005
-2.250 -0.3419 0.01046 0.00383 0.0225 0.8777 0.6273
-2.000 -0.3178 0.01035 0.00374 0.0236 0.8681 0.6530
-1.750 -0.2932 0.01024 0.00367 0.0246 0.8581 0.6755
-1.500 -0.2679 0.01016 0.00361 0.0253 0.8469 0.6963
-1.250 -0.2424 0.01008 0.00354 0.0260 0.8357 0.7150
-1.000 -0.2165 0.01001 0.00348 0.0267 0.8242 0.7326
-0.750 -0.1902 0.00993 0.00342 0.0272 0.8116 0.7493
-0.500 -0.1634 0.00986 0.00337 0.0276 0.7979 0.7656
-0.250 -0.1363 0.00980 0.00332 0.0280 0.7835 0.7811
0.000 -0.1089 0.00974 0.00328 0.0283 0.7685 0.7965
0.250 -0.0810 0.00970 0.00323 0.0285 0.7528 0.8118
0.500 -0.0525 0.00967 0.00319 0.0285 0.7366 0.8270
0.750 -0.0233 0.00966 0.00316 0.0284 0.7203 0.8422
1.000 0.0069 0.00967 0.00315 0.0280 0.7038 0.8570
1.250 0.0390 0.00970 0.00315 0.0272 0.6874 0.8716
1.500 0.0732 0.00975 0.00318 0.0259 0.6712 0.8853
1.750 0.1101 0.00983 0.00325 0.0239 0.6552 0.8981
2.000 0.1513 0.00995 0.00335 0.0209 0.6390 0.9081
2.250 0.1924 0.01008 0.00348 0.0180 0.6223 0.9174
2.500 0.2341 0.01025 0.00362 0.0149 0.6018 0.9254
2.750 0.2757 0.01044 0.00377 0.0118 0.5802 0.9321
3.000 0.3168 0.01064 0.00399 0.0089 0.5612 0.9401
3.250 0.3581 0.01088 0.00425 0.0060 0.5438 0.9488
3.500 0.3963 0.01112 0.00450 0.0038 0.5268 0.9584
3.750 0.4303 0.01137 0.00471 0.0024 0.5003 0.9679
4.250 0.4932 0.01205 0.00512 0.0002 0.4164 0.9881
4.500 0.5265 0.01255 0.00537 -0.0015 0.3479 0.9948
5.000 0.5857 0.01416 0.00612 -0.0041 0.1709 1.0000
5.250 0.6048 0.01510 0.00662 -0.0033 0.0893 1.0000
5.500 0.6249 0.01584 0.00717 -0.0024 0.0583 1.0000
5.750 0.6462 0.01638 0.00770 -0.0015 0.0487 1.0000
6.000 0.6670 0.01699 0.00830 -0.0005 0.0427 1.0000
6.250 0.6885 0.01749 0.00887 0.0004 0.0386 1.0000
6.500 0.7094 0.01808 0.00950 0.0014 0.0353 1.0000
6.750 0.7283 0.01891 0.01035 0.0027 0.0329 1.0000
7.000 0.7487 0.01951 0.01104 0.0038 0.0309 1.0000
7.250 0.7686 0.02016 0.01174 0.0049 0.0288 1.0000
7.500 0.7876 0.02090 0.01251 0.0061 0.0270 1.0000
7.750 0.8034 0.02203 0.01363 0.0077 0.0258 1.0000
8.000 0.8220 0.02286 0.01456 0.0091 0.0249 1.0000
8.250 0.8400 0.02378 0.01557 0.0105 0.0238 1.0000
8.500 0.8580 0.02467 0.01654 0.0119 0.0226 1.0000
8.750 0.8757 0.02553 0.01745 0.0132 0.0215 1.0000
9.000 0.8924 0.02649 0.01843 0.0145 0.0206 1.0000
9.250 0.9077 0.02789 0.01987 0.0161 0.0198 1.0000
9.500 0.9244 0.02911 0.02127 0.0176 0.0193 1.0000
9.750 0.9402 0.03051 0.02283 0.0191 0.0187 1.0000
10.000 0.9549 0.03201 0.02452 0.0207 0.0182 1.0000
10.250 0.9683 0.03362 0.02631 0.0224 0.0177 1.0000
10.500 0.9796 0.03530 0.02820 0.0242 0.0173 1.0000
10.750 0.9890 0.03694 0.03002 0.0262 0.0168 1.0000
11.000 0.9967 0.03846 0.03168 0.0282 0.0164 1.0000
11.250 1.0004 0.03995 0.03330 0.0308 0.0161 1.0000
11.500 1.0013 0.04142 0.03484 0.0335 0.0158 1.0000
11.750 1.0006 0.04337 0.03689 0.0359 0.0155 1.0000
12.000 0.9945 0.04587 0.03961 0.0382 0.0152 1.0000
12.250 0.9851 0.04873 0.04276 0.0401 0.0150 1.0000
12.500 0.9732 0.05217 0.04649 0.0412 0.0148 1.0000
12.750 0.9595 0.05614 0.05071 0.0415 0.0147 1.0000
13.000 0.9437 0.06072 0.05554 0.0408 0.0147 1.0000
13.250 0.9260 0.06599 0.06104 0.0390 0.0146 1.0000
13.500 0.9054 0.07221 0.06748 0.0361 0.0146 1.0000
13.750 0.8835 0.07922 0.07469 0.0323 0.0147 1.0000
14.000 0.8593 0.08733 0.08299 0.0274 0.0147 1.0000
14.250 0.8328 0.09672 0.09254 0.0216 0.0148 1.0000
14.500 0.8029 0.10804 0.10400 0.0147 0.0150 1.0000
14.750 0.7659 0.12269 0.11874 0.0065 0.0152 1.0000
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