Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf) Reynolds number: 1,000,000 Max Cl/Cd: 85.85 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0015-jf-1000000.txt Download as CSV file: xf-joukowsk0015-jf-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=15%
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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.3490 0.08627 0.08233 -0.0023 1.0000 0.0291
-18.500 -1.3669 0.07980 0.07577 -0.0058 1.0000 0.0295
-18.250 -1.3825 0.07381 0.06968 -0.0089 1.0000 0.0298
-18.000 -1.3962 0.06829 0.06408 -0.0117 1.0000 0.0302
-17.750 -1.4068 0.06337 0.05907 -0.0141 1.0000 0.0306
-17.500 -1.4162 0.05879 0.05439 -0.0162 1.0000 0.0310
-17.250 -1.4234 0.05462 0.05014 -0.0180 1.0000 0.0314
-17.000 -1.4303 0.05067 0.04610 -0.0195 1.0000 0.0318
-16.750 -1.4334 0.04729 0.04263 -0.0207 1.0000 0.0323
-16.500 -1.4351 0.04415 0.03940 -0.0217 1.0000 0.0326
-16.250 -1.4387 0.04088 0.03604 -0.0227 1.0000 0.0330
-16.000 -1.4459 0.03735 0.03244 -0.0236 1.0000 0.0337
-15.750 -1.4480 0.03450 0.02952 -0.0241 1.0000 0.0343
-15.500 -1.4468 0.03209 0.02705 -0.0243 1.0000 0.0349
-15.250 -1.4432 0.03004 0.02494 -0.0242 1.0000 0.0355
-15.000 -1.4375 0.02827 0.02311 -0.0240 1.0000 0.0362
-14.750 -1.4292 0.02681 0.02158 -0.0235 1.0000 0.0369
-14.500 -1.4249 0.02515 0.01986 -0.0228 1.0000 0.0377
-14.250 -1.4217 0.02358 0.01824 -0.0217 1.0000 0.0386
-14.000 -1.4153 0.02236 0.01699 -0.0204 1.0000 0.0396
-13.750 -1.4071 0.02139 0.01598 -0.0189 1.0000 0.0406
-13.500 -1.3972 0.02062 0.01516 -0.0172 1.0000 0.0415
-13.250 -1.3889 0.01989 0.01437 -0.0149 1.0000 0.0424
-13.000 -1.3794 0.01912 0.01359 -0.0128 1.0000 0.0438
-12.750 -1.3630 0.01849 0.01295 -0.0115 1.0000 0.0452
-12.500 -1.3435 0.01800 0.01242 -0.0106 1.0000 0.0467
-12.250 -1.3246 0.01741 0.01181 -0.0096 1.0000 0.0484
-12.000 -1.3048 0.01683 0.01123 -0.0087 1.0000 0.0503
-11.750 -1.2829 0.01637 0.01076 -0.0080 1.0000 0.0522
-11.500 -1.2607 0.01589 0.01026 -0.0074 1.0000 0.0542
-11.250 -1.2385 0.01538 0.00976 -0.0067 1.0000 0.0566
-11.000 -1.2145 0.01499 0.00935 -0.0063 1.0000 0.0590
-10.750 -1.1913 0.01451 0.00888 -0.0057 1.0000 0.0619
-10.500 -1.1670 0.01409 0.00848 -0.0053 1.0000 0.0648
-10.250 -1.1421 0.01372 0.00809 -0.0049 1.0000 0.0677
-10.000 -1.1176 0.01329 0.00770 -0.0046 1.0000 0.0715
-9.750 -1.0918 0.01296 0.00736 -0.0043 1.0000 0.0749
-9.500 -1.0667 0.01254 0.00698 -0.0040 1.0000 0.0794
-9.250 -1.0403 0.01224 0.00668 -0.0037 1.0000 0.0833
-9.000 -1.0146 0.01185 0.00633 -0.0035 1.0000 0.0888
-8.750 -0.9880 0.01154 0.00604 -0.0033 1.0000 0.0937
-8.500 -0.9615 0.01120 0.00574 -0.0031 1.0000 0.0997
-8.250 -0.9346 0.01089 0.00546 -0.0030 1.0000 0.1057
-8.000 -0.8987 0.01061 0.00521 -0.0047 0.9619 0.1127
-7.750 -0.8745 0.01038 0.00497 -0.0038 0.9271 0.1199
-7.500 -0.8509 0.01023 0.00475 -0.0028 0.9015 0.1265
-7.250 -0.8260 0.01000 0.00451 -0.0020 0.8795 0.1347
-7.000 -0.8000 0.00980 0.00428 -0.0015 0.8602 0.1428
-6.750 -0.7734 0.00962 0.00408 -0.0011 0.8422 0.1510
-6.500 -0.7467 0.00940 0.00385 -0.0008 0.8254 0.1612
-6.250 -0.7194 0.00922 0.00365 -0.0006 0.8093 0.1706
-5.750 -0.6641 0.00885 0.00329 -0.0002 0.7784 0.1915
-5.500 -0.6361 0.00868 0.00312 -0.0001 0.7639 0.2020
-5.250 -0.6080 0.00855 0.00296 0.0000 0.7497 0.2126
-4.750 -0.5515 0.00822 0.00266 0.0002 0.7215 0.2370
-4.500 -0.5230 0.00810 0.00253 0.0003 0.7081 0.2485
-4.250 -0.4945 0.00799 0.00241 0.0003 0.6944 0.2607
-4.000 -0.4659 0.00785 0.00229 0.0003 0.6810 0.2735
-3.750 -0.4371 0.00774 0.00218 0.0004 0.6682 0.2859
-3.250 -0.3794 0.00754 0.00200 0.0004 0.6419 0.3112
-3.000 -0.3504 0.00745 0.00191 0.0004 0.6292 0.3240
-2.500 -0.2923 0.00731 0.00177 0.0003 0.6034 0.3493
-2.250 -0.2633 0.00723 0.00171 0.0003 0.5910 0.3625
-2.000 -0.2341 0.00719 0.00165 0.0003 0.5777 0.3749
-1.500 -0.1757 0.00709 0.00156 0.0002 0.5529 0.4009
-1.250 -0.1465 0.00705 0.00153 0.0002 0.5398 0.4134
-1.000 -0.1171 0.00703 0.00150 0.0002 0.5274 0.4258
-0.750 -0.0879 0.00700 0.00148 0.0001 0.5151 0.4392
-0.500 -0.0587 0.00698 0.00146 0.0001 0.5020 0.4517
-0.250 -0.0292 0.00697 0.00145 0.0000 0.4897 0.4640
0.000 0.0000 0.00697 0.00145 0.0000 0.4772 0.4771
0.250 0.0293 0.00697 0.00145 0.0000 0.4640 0.4898
0.500 0.0587 0.00698 0.00146 -0.0001 0.4517 0.5019
0.750 0.0879 0.00700 0.00148 -0.0001 0.4392 0.5150
1.000 0.1171 0.00703 0.00150 -0.0002 0.4259 0.5274
1.250 0.1465 0.00705 0.00153 -0.0002 0.4134 0.5398
1.500 0.1757 0.00709 0.00156 -0.0002 0.4008 0.5529
2.000 0.2342 0.00719 0.00165 -0.0003 0.3749 0.5777
2.250 0.2633 0.00723 0.00171 -0.0003 0.3625 0.5909
2.500 0.2923 0.00731 0.00177 -0.0003 0.3493 0.6033
3.000 0.3505 0.00745 0.00191 -0.0004 0.3240 0.6292
3.250 0.3794 0.00754 0.00200 -0.0004 0.3112 0.6418
3.750 0.4371 0.00774 0.00218 -0.0004 0.2858 0.6681
4.000 0.4659 0.00785 0.00229 -0.0003 0.2735 0.6810
4.250 0.4945 0.00799 0.00241 -0.0003 0.2608 0.6943
4.500 0.5230 0.00810 0.00253 -0.0003 0.2484 0.7081
4.750 0.5516 0.00822 0.00266 -0.0002 0.2369 0.7215
5.000 0.5799 0.00838 0.00281 -0.0001 0.2251 0.7352
5.500 0.6362 0.00868 0.00312 0.0001 0.2020 0.7639
5.750 0.6641 0.00885 0.00329 0.0002 0.1914 0.7784
6.250 0.7194 0.00922 0.00365 0.0006 0.1706 0.8093
6.500 0.7466 0.00940 0.00385 0.0008 0.1612 0.8255
6.750 0.7734 0.00962 0.00408 0.0011 0.1510 0.8422
7.000 0.8001 0.00980 0.00428 0.0015 0.1428 0.8601
7.250 0.8260 0.01000 0.00451 0.0020 0.1347 0.8794
7.500 0.8509 0.01023 0.00475 0.0028 0.1265 0.9014
7.750 0.8745 0.01038 0.00497 0.0038 0.1199 0.9271
8.000 0.8987 0.01061 0.00521 0.0047 0.1127 0.9617
8.250 0.9346 0.01089 0.00546 0.0030 0.1056 1.0000
8.500 0.9615 0.01120 0.00574 0.0031 0.0996 1.0000
8.750 0.9879 0.01154 0.00604 0.0033 0.0937 1.0000
9.000 1.0146 0.01185 0.00633 0.0035 0.0888 1.0000
9.250 1.0403 0.01224 0.00668 0.0037 0.0833 1.0000
9.500 1.0666 0.01254 0.00698 0.0040 0.0794 1.0000
9.750 1.0918 0.01296 0.00736 0.0043 0.0748 1.0000
10.000 1.1175 0.01329 0.00770 0.0046 0.0715 1.0000
10.250 1.1422 0.01372 0.00809 0.0049 0.0677 1.0000
10.500 1.1671 0.01409 0.00848 0.0053 0.0648 1.0000
10.750 1.1913 0.01451 0.00888 0.0057 0.0619 1.0000
11.000 1.2145 0.01499 0.00936 0.0063 0.0590 1.0000
11.250 1.2385 0.01537 0.00975 0.0067 0.0566 1.0000
11.500 1.2606 0.01589 0.01026 0.0074 0.0542 1.0000
11.750 1.2828 0.01637 0.01075 0.0080 0.0522 1.0000
12.000 1.3047 0.01683 0.01123 0.0087 0.0503 1.0000
12.250 1.3245 0.01741 0.01181 0.0096 0.0483 1.0000
12.500 1.3436 0.01799 0.01241 0.0106 0.0467 1.0000
12.750 1.3630 0.01849 0.01295 0.0115 0.0452 1.0000
13.000 1.3796 0.01912 0.01359 0.0128 0.0438 1.0000
13.250 1.3892 0.01989 0.01437 0.0149 0.0424 1.0000
13.500 1.3978 0.02061 0.01515 0.0171 0.0415 1.0000
13.750 1.4076 0.02139 0.01598 0.0188 0.0406 1.0000
14.000 1.4160 0.02235 0.01698 0.0203 0.0396 1.0000
14.250 1.4223 0.02357 0.01824 0.0217 0.0388 1.0000
14.500 1.4260 0.02511 0.01982 0.0227 0.0378 1.0000
14.750 1.4298 0.02680 0.02157 0.0235 0.0370 1.0000
15.000 1.4381 0.02825 0.02309 0.0239 0.0362 1.0000
15.250 1.4437 0.03002 0.02492 0.0242 0.0355 1.0000
15.500 1.4475 0.03206 0.02702 0.0242 0.0349 1.0000
15.750 1.4485 0.03448 0.02949 0.0240 0.0342 1.0000
16.000 1.4464 0.03732 0.03240 0.0235 0.0336 1.0000
16.250 1.4396 0.04079 0.03595 0.0227 0.0330 1.0000
16.500 1.4362 0.04405 0.03929 0.0217 0.0326 1.0000
16.750 1.4353 0.04710 0.04243 0.0207 0.0322 1.0000
17.000 1.4315 0.05057 0.04599 0.0195 0.0318 1.0000
17.250 1.4262 0.05432 0.04983 0.0180 0.0313 1.0000
17.500 1.4176 0.05866 0.05427 0.0162 0.0309 1.0000
17.750 1.4085 0.06322 0.05891 0.0141 0.0306 1.0000
18.000 1.3984 0.06808 0.06385 0.0117 0.0301 1.0000
18.250 1.3845 0.07361 0.06948 0.0089 0.0298 1.0000
18.500 1.3686 0.07965 0.07561 0.0058 0.0295 1.0000
18.750 1.3511 0.08607 0.08212 0.0023 0.0291 1.0000
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