ULTIMATE (ultimate-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ULTIMATE (ultimate-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.41 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ultimate-il-1000000.txt Download as CSV file: xf-ultimate-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.1597 0.08977 0.08701 0.0020 1.0000 0.0081
-16.500 -1.1798 0.08236 0.07945 -0.0019 1.0000 0.0082
-16.250 -1.2017 0.07495 0.07186 -0.0055 1.0000 0.0082
-16.000 -1.2168 0.06889 0.06566 -0.0084 1.0000 0.0082
-15.750 -1.2353 0.06262 0.05921 -0.0110 1.0000 0.0083
-15.500 -1.2505 0.05713 0.05357 -0.0130 1.0000 0.0083
-15.250 -1.2613 0.05247 0.04876 -0.0145 1.0000 0.0084
-15.000 -1.2697 0.04831 0.04447 -0.0155 1.0000 0.0085
-14.750 -1.2742 0.04483 0.04087 -0.0161 1.0000 0.0086
-14.500 -1.2749 0.04193 0.03787 -0.0164 1.0000 0.0087
-14.250 -1.2741 0.03932 0.03516 -0.0164 1.0000 0.0088
-14.000 -1.2721 0.03697 0.03271 -0.0160 1.0000 0.0089
-13.750 -1.2676 0.03499 0.03063 -0.0155 1.0000 0.0091
-13.500 -1.2636 0.03306 0.02860 -0.0146 1.0000 0.0092
-13.250 -1.2577 0.03140 0.02685 -0.0135 1.0000 0.0094
-13.000 -1.2503 0.02996 0.02531 -0.0122 1.0000 0.0096
-12.750 -1.2418 0.02868 0.02394 -0.0108 1.0000 0.0097
-12.500 -1.2330 0.02747 0.02264 -0.0092 1.0000 0.0100
-12.250 -1.2234 0.02635 0.02144 -0.0073 1.0000 0.0102
-12.000 -1.2130 0.02533 0.02032 -0.0054 1.0000 0.0104
-11.750 -1.2017 0.02437 0.01927 -0.0034 1.0000 0.0105
-11.500 -1.1896 0.02348 0.01829 -0.0013 1.0000 0.0107
-11.250 -1.1759 0.02273 0.01746 0.0006 1.0000 0.0108
-11.000 -1.1711 0.02134 0.01595 0.0040 1.0000 0.0111
-10.750 -1.1625 0.02004 0.01454 0.0067 1.0000 0.0114
-10.500 -1.1464 0.01922 0.01367 0.0083 1.0000 0.0118
-10.250 -1.1273 0.01858 0.01299 0.0095 1.0000 0.0122
-10.000 -1.1071 0.01800 0.01237 0.0105 1.0000 0.0126
-9.750 -1.0863 0.01744 0.01176 0.0114 1.0000 0.0130
-9.500 -1.0649 0.01690 0.01117 0.0123 1.0000 0.0135
-9.250 -1.0430 0.01639 0.01061 0.0131 1.0000 0.0139
-9.000 -1.0187 0.01608 0.01027 0.0135 1.0000 0.0143
-8.750 -1.0029 0.01505 0.00915 0.0154 1.0000 0.0153
-8.500 -0.9810 0.01456 0.00863 0.0162 1.0000 0.0161
-8.250 -0.9586 0.01416 0.00822 0.0170 1.0000 0.0170
-8.000 -0.9370 0.01380 0.00783 0.0181 1.0000 0.0178
-7.750 -0.9115 0.01349 0.00749 0.0182 0.9986 0.0186
-7.500 -0.8816 0.01282 0.00675 0.0174 0.9957 0.0204
-7.250 -0.8504 0.01243 0.00636 0.0163 0.9921 0.0221
-7.000 -0.8219 0.01217 0.00608 0.0160 0.9856 0.0237
-6.750 -0.8018 0.01188 0.00575 0.0177 0.9751 0.0254
-6.500 -0.7845 0.01157 0.00544 0.0200 0.9639 0.0282
-6.250 -0.7645 0.01133 0.00517 0.0217 0.9541 0.0304
-6.000 -0.7452 0.01102 0.00483 0.0236 0.9448 0.0345
-5.750 -0.7227 0.01073 0.00454 0.0247 0.9352 0.0395
-5.500 -0.7019 0.01033 0.00419 0.0262 0.9264 0.0539
-5.250 -0.6832 0.00975 0.00379 0.0280 0.9175 0.0930
-5.000 -0.6629 0.00914 0.00343 0.0294 0.9090 0.1478
-4.750 -0.6419 0.00868 0.00314 0.0307 0.9014 0.1945
-4.500 -0.6186 0.00824 0.00289 0.0315 0.8940 0.2423
-4.250 -0.5957 0.00788 0.00268 0.0325 0.8870 0.2879
-4.000 -0.5705 0.00758 0.00252 0.0329 0.8802 0.3276
-3.750 -0.5449 0.00739 0.00239 0.0334 0.8735 0.3549
-3.500 -0.5180 0.00724 0.00228 0.0335 0.8670 0.3763
-3.250 -0.4916 0.00707 0.00217 0.0338 0.8599 0.3994
-3.000 -0.4653 0.00689 0.00206 0.0341 0.8532 0.4279
-2.750 -0.4390 0.00668 0.00195 0.0344 0.8458 0.4584
-2.500 -0.4123 0.00652 0.00185 0.0346 0.8383 0.4846
-2.250 -0.3853 0.00636 0.00175 0.0348 0.8298 0.5068
-2.000 -0.3584 0.00620 0.00167 0.0350 0.8211 0.5335
-1.750 -0.3318 0.00604 0.00158 0.0353 0.8111 0.5634
-1.500 -0.3049 0.00589 0.00151 0.0355 0.7992 0.5939
-1.250 -0.2778 0.00578 0.00145 0.0356 0.7861 0.6221
-1.000 -0.2509 0.00568 0.00139 0.0359 0.7706 0.6478
-0.750 -0.2237 0.00562 0.00134 0.0361 0.7529 0.6707
-0.500 -0.1965 0.00558 0.00131 0.0362 0.7343 0.6917
-0.250 -0.1689 0.00557 0.00128 0.0363 0.7149 0.7104
0.000 -0.1412 0.00557 0.00126 0.0364 0.6960 0.7265
0.250 -0.1134 0.00558 0.00125 0.0364 0.6785 0.7410
0.500 -0.0856 0.00559 0.00125 0.0364 0.6621 0.7548
0.750 -0.0577 0.00560 0.00126 0.0363 0.6465 0.7684
1.000 -0.0298 0.00561 0.00127 0.0363 0.6311 0.7823
1.250 -0.0020 0.00563 0.00128 0.0363 0.6139 0.7963
1.500 0.0256 0.00566 0.00131 0.0364 0.5947 0.8113
1.750 0.0532 0.00568 0.00133 0.0364 0.5771 0.8270
2.000 0.0810 0.00570 0.00137 0.0364 0.5622 0.8426
2.250 0.1089 0.00573 0.00141 0.0364 0.5482 0.8587
2.500 0.1372 0.00576 0.00145 0.0363 0.5344 0.8744
2.750 0.1666 0.00577 0.00150 0.0359 0.5214 0.8897
3.000 0.1985 0.00580 0.00154 0.0349 0.5062 0.9051
3.250 0.2377 0.00587 0.00160 0.0322 0.4828 0.9194
3.500 0.2867 0.00602 0.00171 0.0271 0.4562 0.9297
3.750 0.3405 0.00622 0.00185 0.0208 0.4245 0.9354
4.000 0.3890 0.00654 0.00204 0.0158 0.3807 0.9410
4.250 0.4335 0.00697 0.00227 0.0116 0.3244 0.9462
4.500 0.4739 0.00766 0.00262 0.0083 0.2410 0.9514
4.750 0.5113 0.00845 0.00305 0.0055 0.1590 0.9582
5.000 0.5407 0.00946 0.00359 0.0045 0.0645 0.9748
5.250 0.5680 0.01005 0.00407 0.0043 0.0414 0.9911
5.500 0.6037 0.01052 0.00450 0.0023 0.0329 0.9947
5.750 0.6408 0.01079 0.00477 0.0000 0.0297 0.9963
6.000 0.6759 0.01123 0.00521 -0.0019 0.0257 0.9978
6.250 0.7116 0.01147 0.00546 -0.0039 0.0240 0.9991
6.500 0.7443 0.01176 0.00575 -0.0052 0.0222 1.0000
6.750 0.7666 0.01229 0.00631 -0.0044 0.0201 1.0000
7.000 0.7905 0.01257 0.00661 -0.0038 0.0194 1.0000
7.250 0.8145 0.01288 0.00695 -0.0033 0.0185 1.0000
7.500 0.8383 0.01322 0.00730 -0.0027 0.0175 1.0000
7.750 0.8616 0.01362 0.00771 -0.0021 0.0166 1.0000
8.000 0.8806 0.01461 0.00877 -0.0008 0.0153 1.0000
8.250 0.9046 0.01489 0.00907 -0.0003 0.0150 1.0000
8.500 0.9276 0.01527 0.00950 0.0004 0.0144 1.0000
8.750 0.9498 0.01576 0.01003 0.0012 0.0139 1.0000
9.000 0.9718 0.01625 0.01055 0.0020 0.0134 1.0000
9.250 0.9936 0.01674 0.01106 0.0028 0.0129 1.0000
9.500 1.0141 0.01735 0.01170 0.0038 0.0125 1.0000
9.750 1.0304 0.01839 0.01282 0.0054 0.0120 1.0000
10.000 1.0431 0.01984 0.01438 0.0075 0.0116 1.0000
10.250 1.0623 0.02048 0.01509 0.0086 0.0114 1.0000
10.500 1.0807 0.02117 0.01585 0.0099 0.0112 1.0000
10.750 1.0972 0.02202 0.01677 0.0114 0.0110 1.0000
11.000 1.1131 0.02285 0.01769 0.0129 0.0108 1.0000
11.250 1.1274 0.02379 0.01871 0.0147 0.0106 1.0000
11.500 1.1416 0.02465 0.01965 0.0164 0.0103 1.0000
11.750 1.1552 0.02545 0.02051 0.0182 0.0101 1.0000
12.000 1.1644 0.02627 0.02140 0.0207 0.0099 1.0000
12.250 1.1682 0.02709 0.02228 0.0240 0.0097 1.0000
12.500 1.1726 0.02810 0.02336 0.0267 0.0095 1.0000
12.750 1.1775 0.02927 0.02460 0.0290 0.0094 1.0000
13.000 1.1814 0.03070 0.02611 0.0310 0.0093 1.0000
13.250 1.1832 0.03246 0.02796 0.0329 0.0091 1.0000
13.500 1.1796 0.03490 0.03054 0.0346 0.0090 1.0000
13.750 1.1693 0.03827 0.03409 0.0362 0.0088 1.0000
14.000 1.1483 0.04311 0.03920 0.0374 0.0087 1.0000
14.250 1.1462 0.04597 0.04221 0.0373 0.0086 1.0000
14.500 1.1420 0.04929 0.04566 0.0367 0.0086 1.0000
14.750 1.1359 0.05306 0.04958 0.0357 0.0086 1.0000
15.000 1.1284 0.05722 0.05388 0.0343 0.0085 1.0000
15.250 1.1165 0.06221 0.05903 0.0323 0.0085 1.0000
15.500 1.1017 0.06789 0.06486 0.0297 0.0085 1.0000
15.750 1.0847 0.07424 0.07137 0.0266 0.0085 1.0000
16.000 1.0649 0.08148 0.07876 0.0228 0.0085 1.0000
16.250 1.0391 0.09016 0.08762 0.0181 0.0085 1.0000
16.500 1.0078 0.10055 0.09818 0.0124 0.0085 1.0000
16.750 0.9696 0.11312 0.11092 0.0054 0.0086 1.0000
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