ULTIMATE (ultimate-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: ULTIMATE (ultimate-il) Reynolds number: 500,000 Max Cl/Cd: 53.47 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ultimate-il-500000-n5.txt Download as CSV file: xf-ultimate-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0090 0.14085 0.13823 0.0289 1.0000 0.0081
-17.750 -1.0364 0.12985 0.12706 0.0227 1.0000 0.0081
-17.500 -1.0576 0.12076 0.11782 0.0176 1.0000 0.0081
-17.250 -1.0780 0.11224 0.10915 0.0129 1.0000 0.0081
-17.000 -1.0973 0.10420 0.10097 0.0085 1.0000 0.0081
-16.750 -1.1169 0.09643 0.09305 0.0043 1.0000 0.0081
-16.500 -1.1345 0.08928 0.08575 0.0006 1.0000 0.0081
-16.250 -1.1513 0.08246 0.07879 -0.0028 1.0000 0.0082
-16.000 -1.1653 0.07630 0.07248 -0.0059 1.0000 0.0082
-15.750 -1.1778 0.07060 0.06664 -0.0086 1.0000 0.0082
-15.500 -1.1896 0.06520 0.06110 -0.0111 1.0000 0.0083
-15.250 -1.1986 0.06041 0.05617 -0.0131 1.0000 0.0084
-15.000 -1.2055 0.05608 0.05171 -0.0148 1.0000 0.0085
-14.750 -1.2111 0.05211 0.04759 -0.0160 1.0000 0.0085
-14.500 -1.2136 0.04869 0.04404 -0.0170 1.0000 0.0086
-14.250 -1.2152 0.04555 0.04078 -0.0175 1.0000 0.0087
-14.000 -1.2153 0.04270 0.03781 -0.0178 1.0000 0.0088
-13.750 -1.2138 0.04016 0.03515 -0.0177 1.0000 0.0089
-13.500 -1.2119 0.03779 0.03265 -0.0173 1.0000 0.0090
-13.250 -1.2079 0.03574 0.03049 -0.0167 1.0000 0.0092
-13.000 -1.2032 0.03387 0.02849 -0.0158 1.0000 0.0094
-12.750 -1.1981 0.03212 0.02662 -0.0146 1.0000 0.0095
-12.500 -1.1918 0.03055 0.02494 -0.0132 1.0000 0.0097
-12.250 -1.1846 0.02913 0.02340 -0.0116 1.0000 0.0099
-12.000 -1.1763 0.02786 0.02201 -0.0098 1.0000 0.0102
-11.750 -1.1670 0.02670 0.02073 -0.0079 1.0000 0.0104
-11.500 -1.1569 0.02564 0.01955 -0.0059 1.0000 0.0106
-11.250 -1.1454 0.02469 0.01849 -0.0038 1.0000 0.0108
-11.000 -1.1365 0.02362 0.01734 -0.0014 1.0000 0.0111
-10.750 -1.1256 0.02272 0.01638 0.0010 1.0000 0.0114
-10.500 -1.1103 0.02203 0.01565 0.0026 1.0000 0.0119
-10.250 -1.0932 0.02136 0.01491 0.0040 1.0000 0.0123
-10.000 -1.0754 0.02068 0.01415 0.0054 1.0000 0.0127
-9.750 -1.0571 0.02000 0.01340 0.0067 1.0000 0.0132
-9.500 -1.0382 0.01934 0.01267 0.0079 1.0000 0.0137
-9.250 -1.0184 0.01873 0.01198 0.0090 1.0000 0.0142
-9.000 -0.9996 0.01802 0.01121 0.0103 1.0000 0.0148
-8.750 -0.9796 0.01739 0.01054 0.0113 1.0000 0.0155
-8.500 -0.9583 0.01688 0.00999 0.0122 1.0000 0.0163
-8.250 -0.9366 0.01642 0.00949 0.0131 1.0000 0.0173
-8.000 -0.9146 0.01600 0.00902 0.0140 1.0000 0.0182
-7.750 -0.8922 0.01552 0.00850 0.0147 0.9971 0.0194
-7.500 -0.8635 0.01502 0.00798 0.0141 0.9918 0.0210
-7.250 -0.8350 0.01462 0.00753 0.0136 0.9862 0.0226
-7.000 -0.8083 0.01427 0.00713 0.0136 0.9794 0.0241
-6.750 -0.7840 0.01386 0.00671 0.0141 0.9719 0.0266
-6.500 -0.7613 0.01353 0.00636 0.0150 0.9622 0.0294
-6.250 -0.7389 0.01321 0.00601 0.0161 0.9519 0.0326
-6.000 -0.7175 0.01287 0.00567 0.0174 0.9404 0.0376
-5.750 -0.6968 0.01254 0.00534 0.0189 0.9281 0.0445
-5.500 -0.6770 0.01218 0.00499 0.0206 0.9163 0.0569
-5.250 -0.6568 0.01173 0.00463 0.0222 0.9056 0.0810
-5.000 -0.6368 0.01120 0.00426 0.0236 0.8965 0.1214
-4.750 -0.6160 0.01072 0.00394 0.0250 0.8880 0.1631
-4.500 -0.5931 0.01031 0.00365 0.0259 0.8803 0.2014
-4.250 -0.5705 0.00992 0.00339 0.0268 0.8727 0.2426
-4.000 -0.5467 0.00954 0.00318 0.0275 0.8652 0.2874
-3.750 -0.5229 0.00923 0.00300 0.0282 0.8578 0.3294
-3.500 -0.4981 0.00893 0.00285 0.0288 0.8502 0.3707
-3.250 -0.4732 0.00869 0.00271 0.0293 0.8425 0.4061
-3.000 -0.4467 0.00852 0.00258 0.0296 0.8341 0.4262
-2.750 -0.4202 0.00839 0.00244 0.0299 0.8255 0.4416
-2.500 -0.3933 0.00824 0.00233 0.0301 0.8155 0.4585
-2.250 -0.3667 0.00809 0.00221 0.0303 0.8048 0.4768
-2.000 -0.3402 0.00795 0.00210 0.0306 0.7929 0.4973
-1.750 -0.3140 0.00780 0.00199 0.0310 0.7793 0.5213
-1.500 -0.2881 0.00764 0.00189 0.0314 0.7636 0.5504
-1.250 -0.2623 0.00750 0.00182 0.0319 0.7468 0.5820
-1.000 -0.2363 0.00740 0.00175 0.0323 0.7290 0.6116
-0.750 -0.2098 0.00734 0.00170 0.0326 0.7107 0.6369
-0.500 -0.1831 0.00730 0.00166 0.0329 0.6935 0.6577
-0.250 -0.1560 0.00729 0.00164 0.0331 0.6771 0.6760
0.000 -0.1288 0.00728 0.00162 0.0332 0.6615 0.6929
0.250 -0.1013 0.00728 0.00161 0.0333 0.6469 0.7084
0.500 -0.0737 0.00728 0.00161 0.0334 0.6327 0.7230
0.750 -0.0461 0.00729 0.00162 0.0334 0.6189 0.7371
1.000 -0.0184 0.00730 0.00164 0.0334 0.6056 0.7505
1.250 0.0093 0.00732 0.00166 0.0335 0.5926 0.7638
1.500 0.0370 0.00734 0.00169 0.0335 0.5794 0.7777
2.000 0.0923 0.00740 0.00177 0.0336 0.5452 0.8066
2.250 0.1200 0.00745 0.00182 0.0336 0.5260 0.8219
2.500 0.1480 0.00750 0.00188 0.0335 0.5114 0.8374
2.750 0.1765 0.00754 0.00196 0.0333 0.4984 0.8534
3.000 0.2058 0.00759 0.00203 0.0330 0.4860 0.8688
3.250 0.2366 0.00764 0.00211 0.0322 0.4733 0.8842
3.750 0.3099 0.00793 0.00234 0.0279 0.4172 0.9118
4.000 0.3595 0.00825 0.00253 0.0225 0.3667 0.9230
4.250 0.4143 0.00898 0.00288 0.0156 0.2663 0.9324
4.500 0.4633 0.00981 0.00335 0.0101 0.1821 0.9413
4.750 0.5045 0.01058 0.00383 0.0066 0.1117 0.9486
5.000 0.5399 0.01134 0.00432 0.0043 0.0563 0.9553
5.250 0.5737 0.01180 0.00472 0.0027 0.0413 0.9631
5.500 0.5969 0.01221 0.00511 0.0035 0.0352 0.9846
5.750 0.6265 0.01261 0.00552 0.0028 0.0310 0.9924
6.250 0.6935 0.01341 0.00632 -0.0004 0.0247 0.9978
6.500 0.7276 0.01378 0.00673 -0.0021 0.0227 0.9996
6.750 0.7538 0.01417 0.00713 -0.0022 0.0211 1.0000
7.000 0.7763 0.01464 0.00761 -0.0014 0.0197 1.0000
7.250 0.7995 0.01499 0.00800 -0.0007 0.0186 1.0000
7.500 0.8224 0.01538 0.00843 0.0000 0.0175 1.0000
7.750 0.8449 0.01582 0.00890 0.0007 0.0166 1.0000
8.000 0.8664 0.01637 0.00947 0.0016 0.0157 1.0000
8.250 0.8871 0.01701 0.01015 0.0025 0.0151 1.0000
8.500 0.9085 0.01754 0.01076 0.0035 0.0146 1.0000
8.750 0.9291 0.01813 0.01141 0.0045 0.0140 1.0000
9.000 0.9493 0.01874 0.01207 0.0055 0.0135 1.0000
9.250 0.9693 0.01933 0.01271 0.0066 0.0130 1.0000
9.500 0.9890 0.01992 0.01334 0.0076 0.0125 1.0000
9.750 1.0071 0.02064 0.01409 0.0089 0.0120 1.0000
10.000 1.0224 0.02159 0.01511 0.0105 0.0116 1.0000
10.250 1.0397 0.02232 0.01593 0.0119 0.0113 1.0000
10.500 1.0555 0.02314 0.01685 0.0135 0.0110 1.0000
10.750 1.0699 0.02404 0.01784 0.0153 0.0107 1.0000
11.000 1.0834 0.02497 0.01887 0.0171 0.0105 1.0000
11.250 1.0955 0.02597 0.01996 0.0190 0.0102 1.0000
11.500 1.1049 0.02696 0.02103 0.0214 0.0100 1.0000
11.750 1.1093 0.02796 0.02213 0.0245 0.0098 1.0000
12.000 1.1140 0.02906 0.02333 0.0272 0.0097 1.0000
12.250 1.1193 0.03027 0.02463 0.0295 0.0095 1.0000
12.500 1.1248 0.03160 0.02604 0.0313 0.0093 1.0000
12.750 1.1295 0.03310 0.02764 0.0330 0.0092 1.0000
13.000 1.1331 0.03483 0.02947 0.0344 0.0091 1.0000
13.250 1.1351 0.03681 0.03156 0.0355 0.0090 1.0000
13.500 1.1347 0.03919 0.03404 0.0364 0.0088 1.0000
13.750 1.1311 0.04206 0.03706 0.0370 0.0087 1.0000
14.000 1.1283 0.04504 0.04019 0.0372 0.0086 1.0000
14.250 1.1256 0.04819 0.04350 0.0369 0.0086 1.0000
14.500 1.1213 0.05169 0.04718 0.0362 0.0085 1.0000
14.750 1.1152 0.05563 0.05129 0.0351 0.0084 1.0000
15.000 1.1075 0.05993 0.05576 0.0336 0.0084 1.0000
15.250 1.0969 0.06487 0.06087 0.0316 0.0083 1.0000
15.500 1.0837 0.07039 0.06656 0.0291 0.0083 1.0000
15.750 1.0686 0.07655 0.07289 0.0261 0.0082 1.0000
16.000 1.0512 0.08341 0.07992 0.0226 0.0082 1.0000
16.250 1.0298 0.09135 0.08803 0.0184 0.0082 1.0000
16.500 1.0046 0.10054 0.09740 0.0134 0.0082 1.0000
16.750 0.9760 0.11095 0.10797 0.0078 0.0082 1.0000
17.000 0.9362 0.12458 0.12179 0.0005 0.0083 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ULTIMATE (ultimate-il)