Joukovsky f=0% t=18% (joukowsk0018-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=18% (joukowsk0018-jf) Reynolds number: 50,000 Max Cl/Cd: 23.03 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk0018-jf-50000-n5.txt Download as CSV file: xf-joukowsk0018-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=18%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6373 0.11884 0.10985 0.0055 1.0000 0.1580
-12.750 -0.6760 0.10728 0.09826 -0.0008 1.0000 0.1648
-12.250 -0.7231 0.09039 0.08130 -0.0093 1.0000 0.1778
-12.000 -0.6898 0.09246 0.08339 -0.0071 1.0000 0.1799
-11.750 -0.8322 0.06659 0.05726 -0.0217 1.0000 0.1923
-11.500 -0.7594 0.07347 0.06430 -0.0166 1.0000 0.1947
-11.250 -0.7485 0.07167 0.06251 -0.0167 1.0000 0.1995
-11.000 -0.8911 0.05181 0.04215 -0.0263 1.0000 0.2074
-10.750 -0.8468 0.05345 0.04398 -0.0248 1.0000 0.2127
-10.500 -0.8675 0.04917 0.03956 -0.0254 1.0000 0.2183
-10.250 -0.8935 0.04513 0.03532 -0.0247 1.0000 0.2235
-10.000 -0.8647 0.04512 0.03545 -0.0241 1.0000 0.2293
-9.750 -0.8731 0.04281 0.03302 -0.0226 1.0000 0.2354
-9.500 -0.8677 0.04124 0.03140 -0.0214 1.0000 0.2416
-9.250 -0.8502 0.04051 0.03073 -0.0206 1.0000 0.2483
-9.000 -0.8551 0.03825 0.02824 -0.0191 1.0000 0.2560
-8.750 -0.8273 0.03814 0.02831 -0.0185 1.0000 0.2625
-8.500 -0.8194 0.03674 0.02682 -0.0174 1.0000 0.2707
-8.250 -0.8008 0.03603 0.02617 -0.0165 1.0000 0.2779
-8.000 -0.7855 0.03519 0.02533 -0.0155 1.0000 0.2862
-7.750 -0.7718 0.03422 0.02434 -0.0144 1.0000 0.2943
-7.500 -0.7534 0.03373 0.02393 -0.0134 1.0000 0.3023
-7.250 -0.7454 0.03268 0.02281 -0.0118 1.0000 0.3111
-7.000 -0.7293 0.03246 0.02273 -0.0101 1.0000 0.3182
-6.750 -0.7296 0.03168 0.02189 -0.0071 1.0000 0.3264
-6.500 -0.7101 0.03141 0.02170 -0.0065 0.9923 0.3342
-6.250 -0.6720 0.03057 0.02070 -0.0099 0.9723 0.3477
-6.000 -0.6269 0.03051 0.02077 -0.0128 0.9566 0.3580
-5.750 -0.5885 0.02995 0.02013 -0.0154 0.9394 0.3704
-5.500 -0.5509 0.02964 0.01981 -0.0174 0.9227 0.3820
-5.250 -0.5162 0.02936 0.01953 -0.0186 0.9059 0.3928
-5.000 -0.4877 0.02892 0.01897 -0.0191 0.8886 0.4050
-4.750 -0.4567 0.02887 0.01897 -0.0192 0.8725 0.4144
-4.500 -0.4337 0.02839 0.01831 -0.0187 0.8565 0.4270
-4.250 -0.4055 0.02847 0.01849 -0.0179 0.8408 0.4354
-4.000 -0.3854 0.02807 0.01795 -0.0170 0.8246 0.4478
-3.750 -0.3588 0.02814 0.01809 -0.0159 0.8101 0.4562
-3.500 -0.3375 0.02777 0.01758 -0.0148 0.7968 0.4688
-3.250 -0.3123 0.02785 0.01774 -0.0136 0.7816 0.4773
-3.000 -0.2911 0.02754 0.01731 -0.0126 0.7681 0.4898
-2.750 -0.2654 0.02759 0.01741 -0.0112 0.7554 0.4986
-2.500 -0.2439 0.02734 0.01707 -0.0104 0.7414 0.5111
-2.250 -0.2181 0.02737 0.01713 -0.0090 0.7302 0.5201
-2.000 -0.1961 0.02717 0.01687 -0.0082 0.7160 0.5326
-1.750 -0.1706 0.02722 0.01696 -0.0069 0.7043 0.5417
-1.500 -0.1479 0.02704 0.01671 -0.0060 0.6915 0.5544
-1.250 -0.1226 0.02711 0.01683 -0.0048 0.6795 0.5638
-1.000 -0.0992 0.02694 0.01659 -0.0039 0.6677 0.5765
-0.750 -0.0738 0.02703 0.01674 -0.0029 0.6554 0.5862
-0.500 -0.0496 0.02688 0.01652 -0.0020 0.6444 0.5988
-0.250 -0.0246 0.02699 0.01669 -0.0010 0.6319 0.6089
0.000 0.0000 0.02686 0.01650 0.0000 0.6214 0.6214
0.250 0.0246 0.02699 0.01669 0.0010 0.6089 0.6319
0.500 0.0495 0.02688 0.01652 0.0020 0.5988 0.6444
0.750 0.0738 0.02703 0.01674 0.0029 0.5862 0.6554
1.000 0.0992 0.02694 0.01659 0.0039 0.5765 0.6677
1.250 0.1226 0.02711 0.01683 0.0048 0.5638 0.6795
1.500 0.1478 0.02704 0.01671 0.0060 0.5545 0.6915
1.750 0.1706 0.02722 0.01696 0.0069 0.5417 0.7043
2.000 0.1961 0.02717 0.01687 0.0082 0.5326 0.7160
2.250 0.2181 0.02737 0.01713 0.0090 0.5200 0.7302
2.500 0.2439 0.02734 0.01707 0.0104 0.5111 0.7414
2.750 0.2654 0.02759 0.01741 0.0112 0.4986 0.7554
3.000 0.2911 0.02754 0.01731 0.0126 0.4898 0.7681
3.250 0.3123 0.02785 0.01774 0.0136 0.4773 0.7816
3.500 0.3375 0.02777 0.01758 0.0148 0.4688 0.7968
3.750 0.3588 0.02814 0.01809 0.0159 0.4563 0.8102
4.000 0.3854 0.02807 0.01795 0.0170 0.4478 0.8246
4.250 0.4055 0.02847 0.01849 0.0179 0.4354 0.8408
4.500 0.4337 0.02839 0.01832 0.0187 0.4270 0.8565
4.750 0.4567 0.02888 0.01897 0.0192 0.4144 0.8726
5.000 0.4877 0.02892 0.01897 0.0191 0.4050 0.8887
5.250 0.5163 0.02936 0.01953 0.0186 0.3928 0.9059
5.500 0.5509 0.02964 0.01981 0.0173 0.3820 0.9227
5.750 0.5886 0.02994 0.02012 0.0154 0.3704 0.9395
6.000 0.6269 0.03051 0.02077 0.0128 0.3579 0.9567
6.250 0.6721 0.03057 0.02070 0.0099 0.3477 0.9723
6.500 0.7102 0.03140 0.02170 0.0065 0.3343 0.9924
6.750 0.7296 0.03168 0.02188 0.0071 0.3265 1.0000
7.000 0.7292 0.03246 0.02273 0.0101 0.3182 1.0000
7.250 0.7453 0.03269 0.02282 0.0118 0.3111 1.0000
7.500 0.7535 0.03373 0.02393 0.0134 0.3023 1.0000
7.750 0.7719 0.03422 0.02433 0.0144 0.2943 1.0000
8.000 0.7856 0.03519 0.02532 0.0155 0.2862 1.0000
8.250 0.8010 0.03602 0.02616 0.0165 0.2779 1.0000
8.500 0.8194 0.03674 0.02682 0.0174 0.2706 1.0000
8.750 0.8276 0.03813 0.02831 0.0185 0.2625 1.0000
9.000 0.8554 0.03824 0.02822 0.0190 0.2559 1.0000
9.250 0.8505 0.04050 0.03072 0.0205 0.2482 1.0000
9.500 0.8683 0.04121 0.03138 0.0214 0.2416 1.0000
9.750 0.8733 0.04281 0.03302 0.0226 0.2353 1.0000
10.000 0.8654 0.04510 0.03543 0.0241 0.2292 1.0000
10.250 0.8946 0.04507 0.03526 0.0247 0.2234 1.0000
10.500 0.8679 0.04917 0.03956 0.0253 0.2182 1.0000
10.750 0.8484 0.05335 0.04388 0.0248 0.2126 1.0000
11.000 0.8936 0.05165 0.04198 0.0263 0.2074 1.0000
11.250 0.7526 0.07120 0.06203 0.0169 0.1996 1.0000
11.500 0.7627 0.07311 0.06393 0.0167 0.1948 1.0000
11.750 0.8343 0.06642 0.05709 0.0217 0.1923 1.0000
12.250 0.7139 0.09224 0.08315 0.0080 0.1770 1.0000
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Polar data table (+)
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