ULTIMATE (ultimate-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ULTIMATE (ultimate-il) Reynolds number: 500,000 Max Cl/Cd: 55.43 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ultimate-il-500000.txt Download as CSV file: xf-ultimate-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9809 0.08758 0.08465 -0.0080 1.0000 0.0142
-14.500 -1.0066 0.07927 0.07618 -0.0129 1.0000 0.0142
-14.250 -1.0290 0.07213 0.06884 -0.0168 1.0000 0.0141
-14.000 -1.0492 0.06585 0.06238 -0.0199 1.0000 0.0141
-13.750 -1.0652 0.06075 0.05707 -0.0220 1.0000 0.0142
-13.500 -1.0781 0.05648 0.05261 -0.0232 1.0000 0.0142
-13.250 -1.0915 0.05247 0.04838 -0.0236 1.0000 0.0143
-12.750 -1.1171 0.04529 0.04073 -0.0217 1.0000 0.0144
-12.500 -1.1293 0.04137 0.03653 -0.0196 1.0000 0.0145
-12.250 -1.1343 0.03812 0.03304 -0.0174 1.0000 0.0147
-12.000 -1.1329 0.03560 0.03037 -0.0153 1.0000 0.0149
-11.750 -1.1273 0.03377 0.02842 -0.0133 1.0000 0.0152
-11.500 -1.1197 0.03222 0.02676 -0.0112 1.0000 0.0154
-11.250 -1.1107 0.03086 0.02529 -0.0091 1.0000 0.0157
-11.000 -1.1005 0.02958 0.02390 -0.0070 1.0000 0.0161
-10.750 -1.0889 0.02834 0.02254 -0.0050 1.0000 0.0164
-10.500 -1.0753 0.02717 0.02126 -0.0032 1.0000 0.0169
-10.250 -1.0598 0.02596 0.01993 -0.0017 1.0000 0.0173
-10.000 -1.0429 0.02493 0.01879 -0.0003 1.0000 0.0179
-9.750 -1.0245 0.02414 0.01788 0.0010 1.0000 0.0184
-9.500 -1.0085 0.02270 0.01632 0.0025 1.0000 0.0191
-9.250 -0.9942 0.02122 0.01479 0.0043 1.0000 0.0199
-9.000 -0.9760 0.02037 0.01391 0.0056 1.0000 0.0207
-8.750 -0.9569 0.01960 0.01309 0.0068 1.0000 0.0215
-8.500 -0.9373 0.01887 0.01230 0.0080 1.0000 0.0225
-8.250 -0.9171 0.01822 0.01158 0.0092 1.0000 0.0235
-8.000 -0.8954 0.01773 0.01102 0.0101 1.0000 0.0242
-7.750 -0.8835 0.01646 0.00971 0.0127 1.0000 0.0261
-7.500 -0.8644 0.01596 0.00919 0.0141 1.0000 0.0278
-7.250 -0.8470 0.01553 0.00872 0.0159 1.0000 0.0296
-7.000 -0.8321 0.01520 0.00834 0.0183 1.0000 0.0309
-6.750 -0.8259 0.01457 0.00766 0.0223 1.0000 0.0331
-6.500 -0.7982 0.01403 0.00711 0.0219 0.9977 0.0366
-6.250 -0.7641 0.01348 0.00651 0.0203 0.9953 0.0418
-6.000 -0.7300 0.01290 0.00595 0.0186 0.9927 0.0506
-5.750 -0.6992 0.01195 0.00526 0.0174 0.9891 0.0921
-5.500 -0.6703 0.01084 0.00466 0.0163 0.9854 0.1875
-5.250 -0.6436 0.01018 0.00431 0.0161 0.9791 0.2540
-5.000 -0.6161 0.00970 0.00407 0.0158 0.9734 0.3122
-4.750 -0.5929 0.00941 0.00391 0.0168 0.9647 0.3498
-4.500 -0.5691 0.00921 0.00376 0.0177 0.9573 0.3777
-4.250 -0.5471 0.00899 0.00360 0.0190 0.9485 0.4015
-4.000 -0.5246 0.00880 0.00345 0.0202 0.9404 0.4242
-3.750 -0.5037 0.00856 0.00328 0.0219 0.9324 0.4493
-3.500 -0.4819 0.00831 0.00313 0.0233 0.9236 0.4806
-3.250 -0.4615 0.00806 0.00298 0.0251 0.9158 0.5124
-3.000 -0.4386 0.00785 0.00285 0.0262 0.9066 0.5389
-2.750 -0.4160 0.00767 0.00273 0.0276 0.8983 0.5658
-2.500 -0.3929 0.00752 0.00263 0.0287 0.8893 0.5948
-2.250 -0.3688 0.00739 0.00256 0.0297 0.8801 0.6233
-1.750 -0.3196 0.00719 0.00244 0.0315 0.8613 0.6736
-1.500 -0.2943 0.00711 0.00240 0.0322 0.8515 0.6965
-1.250 -0.2689 0.00704 0.00235 0.0329 0.8418 0.7172
-1.000 -0.2425 0.00695 0.00230 0.0333 0.8303 0.7364
-0.750 -0.2159 0.00687 0.00225 0.0338 0.8183 0.7540
-0.500 -0.1892 0.00680 0.00219 0.0342 0.8058 0.7701
-0.250 -0.1623 0.00673 0.00214 0.0345 0.7918 0.7855
0.000 -0.1352 0.00667 0.00209 0.0348 0.7763 0.8007
0.250 -0.1080 0.00663 0.00205 0.0351 0.7594 0.8159
0.500 -0.0806 0.00661 0.00201 0.0354 0.7413 0.8310
0.750 -0.0531 0.00661 0.00199 0.0356 0.7229 0.8462
1.000 -0.0253 0.00663 0.00198 0.0357 0.7051 0.8612
1.250 0.0035 0.00665 0.00198 0.0355 0.6875 0.8762
1.500 0.0338 0.00666 0.00198 0.0350 0.6702 0.8913
1.750 0.0680 0.00669 0.00200 0.0336 0.6522 0.9061
2.000 0.1088 0.00676 0.00204 0.0305 0.6309 0.9193
2.250 0.1553 0.00688 0.00213 0.0262 0.6111 0.9295
2.500 0.2062 0.00702 0.00227 0.0208 0.5931 0.9351
2.750 0.2522 0.00719 0.00243 0.0166 0.5762 0.9415
3.000 0.2958 0.00740 0.00262 0.0130 0.5593 0.9463
3.250 0.3355 0.00765 0.00280 0.0103 0.5345 0.9519
3.500 0.3728 0.00789 0.00299 0.0082 0.5093 0.9581
3.750 0.4080 0.00816 0.00319 0.0065 0.4818 0.9654
4.000 0.4411 0.00846 0.00341 0.0052 0.4512 0.9766
4.250 0.4754 0.00885 0.00369 0.0036 0.4163 0.9876
4.500 0.5144 0.00928 0.00395 0.0008 0.3646 0.9932
4.750 0.5514 0.01000 0.00426 -0.0018 0.2690 0.9962
5.000 0.5852 0.01119 0.00477 -0.0043 0.1339 0.9982
5.250 0.6192 0.01235 0.00547 -0.0065 0.0507 0.9999
5.500 0.6408 0.01283 0.00592 -0.0057 0.0421 1.0000
5.750 0.6626 0.01308 0.00620 -0.0048 0.0385 1.0000
6.000 0.6840 0.01353 0.00664 -0.0038 0.0347 1.0000
6.250 0.7052 0.01412 0.00729 -0.0028 0.0323 1.0000
6.500 0.7277 0.01453 0.00774 -0.0020 0.0303 1.0000
6.750 0.7499 0.01499 0.00820 -0.0011 0.0283 1.0000
7.000 0.7685 0.01597 0.00920 0.0002 0.0261 1.0000
7.250 0.7899 0.01656 0.00984 0.0012 0.0250 1.0000
7.500 0.8112 0.01714 0.01049 0.0022 0.0239 1.0000
7.750 0.8319 0.01779 0.01118 0.0033 0.0228 1.0000
8.000 0.8524 0.01846 0.01187 0.0043 0.0218 1.0000
8.250 0.8715 0.01932 0.01275 0.0056 0.0210 1.0000
8.500 0.8857 0.02128 0.01476 0.0075 0.0200 1.0000
8.750 0.9064 0.02189 0.01547 0.0085 0.0195 1.0000
9.000 0.9264 0.02264 0.01632 0.0097 0.0188 1.0000
9.250 0.9455 0.02358 0.01735 0.0109 0.0181 1.0000
9.500 0.9638 0.02466 0.01853 0.0122 0.0176 1.0000
9.750 0.9815 0.02579 0.01975 0.0135 0.0172 1.0000
10.000 0.9983 0.02694 0.02100 0.0149 0.0167 1.0000
10.250 1.0141 0.02818 0.02234 0.0164 0.0164 1.0000
10.500 1.0287 0.02959 0.02384 0.0179 0.0160 1.0000
10.750 1.0406 0.03168 0.02606 0.0196 0.0157 1.0000
11.000 1.0464 0.03495 0.02958 0.0218 0.0155 1.0000
11.250 1.0464 0.03844 0.03337 0.0246 0.0154 1.0000
11.500 1.0433 0.04086 0.03606 0.0278 0.0153 1.0000
11.750 1.0363 0.04251 0.03790 0.0318 0.0151 1.0000
12.000 1.0252 0.04448 0.04007 0.0356 0.0150 1.0000
12.250 1.0130 0.04704 0.04283 0.0384 0.0149 1.0000
12.500 0.9974 0.05046 0.04647 0.0401 0.0149 1.0000
12.750 0.9809 0.05430 0.05052 0.0408 0.0148 1.0000
13.000 0.9620 0.05892 0.05535 0.0403 0.0148 1.0000
13.250 0.9418 0.06428 0.06090 0.0386 0.0148 1.0000
13.500 0.9186 0.07073 0.06753 0.0357 0.0149 1.0000
13.750 0.8944 0.07798 0.07493 0.0318 0.0150 1.0000
14.000 0.8684 0.08624 0.08333 0.0270 0.0151 1.0000
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