WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 50,000 Max Cl/Cd: 19.87 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-whitcomb-il-50000-n5.txt Download as CSV file: xf-whitcomb-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6911 0.08778 0.07909 -0.0459 1.0000 0.0714
-10.750 -0.7187 0.08112 0.07238 -0.0485 1.0000 0.0711
-10.500 -0.7472 0.07560 0.06679 -0.0496 1.0000 0.0709
-10.250 -0.7755 0.07118 0.06229 -0.0491 1.0000 0.0707
-10.000 -0.8016 0.06726 0.05824 -0.0479 1.0000 0.0707
-9.750 -0.8202 0.06290 0.05368 -0.0480 1.0000 0.0708
-9.500 -0.8325 0.05866 0.04909 -0.0480 1.0000 0.0712
-9.250 -0.8310 0.05551 0.04575 -0.0475 1.0000 0.0722
-9.000 -0.8217 0.05334 0.04352 -0.0468 1.0000 0.0738
-8.750 -0.8122 0.05098 0.04101 -0.0464 1.0000 0.0757
-8.500 -0.8023 0.04819 0.03793 -0.0462 1.0000 0.0778
-8.250 -0.7899 0.04520 0.03453 -0.0461 1.0000 0.0800
-8.000 -0.7741 0.04239 0.03122 -0.0461 1.0000 0.0824
-7.750 -0.7556 0.04084 0.02973 -0.0454 1.0000 0.0852
-7.500 -0.7362 0.03919 0.02793 -0.0449 1.0000 0.0888
-7.250 -0.7156 0.03734 0.02577 -0.0443 1.0000 0.0926
-7.000 -0.6951 0.03586 0.02420 -0.0434 1.0000 0.0966
-6.750 -0.6742 0.03468 0.02300 -0.0425 1.0000 0.1015
-6.500 -0.6526 0.03345 0.02152 -0.0412 1.0000 0.1071
-6.250 -0.6324 0.03247 0.02068 -0.0397 1.0000 0.1127
-6.000 -0.6113 0.03161 0.01969 -0.0381 1.0000 0.1203
-5.750 -0.5914 0.03079 0.01895 -0.0363 1.0000 0.1278
-5.500 -0.5708 0.03003 0.01813 -0.0347 1.0000 0.1382
-5.250 -0.5506 0.02922 0.01742 -0.0333 1.0000 0.1498
-5.000 -0.5299 0.02840 0.01672 -0.0322 1.0000 0.1646
-4.750 -0.5082 0.02756 0.01600 -0.0315 1.0000 0.1844
-4.500 -0.4855 0.02661 0.01528 -0.0313 1.0000 0.2112
-4.250 -0.4610 0.02551 0.01453 -0.0318 1.0000 0.2518
-4.000 -0.4345 0.02425 0.01387 -0.0330 1.0000 0.3213
-3.500 -0.4233 0.02554 0.01666 -0.0186 1.0000 0.4952
-3.000 -0.3768 0.02732 0.01821 -0.0150 1.0000 0.6285
-2.750 -0.3475 0.02797 0.01864 -0.0155 1.0000 0.6663
-2.500 -0.3286 0.02857 0.01913 -0.0128 1.0000 0.6896
-2.250 -0.3131 0.02898 0.01947 -0.0092 1.0000 0.7087
-2.000 -0.2976 0.02921 0.01965 -0.0058 1.0000 0.7266
-1.750 -0.2816 0.02929 0.01967 -0.0027 1.0000 0.7429
-1.500 -0.2653 0.02926 0.01959 0.0002 1.0000 0.7582
-1.250 -0.2501 0.02917 0.01947 0.0034 1.0000 0.7743
-1.000 -0.2360 0.02902 0.01930 0.0068 1.0000 0.7910
-0.750 -0.2216 0.02879 0.01905 0.0099 1.0000 0.8072
-0.500 -0.2046 0.02850 0.01875 0.0122 1.0000 0.8205
-0.250 -0.1804 0.02829 0.01850 0.0122 1.0000 0.8289
0.000 -0.1593 0.02795 0.01815 0.0131 1.0000 0.8344
0.250 -0.1360 0.02772 0.01792 0.0133 1.0000 0.8397
0.500 -0.1088 0.02762 0.01782 0.0124 1.0000 0.8444
0.750 -0.0855 0.02741 0.01765 0.0126 1.0000 0.8480
1.000 -0.0613 0.02727 0.01755 0.0125 1.0000 0.8514
1.250 -0.0351 0.02723 0.01756 0.0119 1.0000 0.8543
1.500 -0.0075 0.02726 0.01767 0.0109 1.0000 0.8569
1.750 0.0210 0.02738 0.01788 0.0096 1.0000 0.8592
2.000 0.0624 0.02771 0.01833 0.0059 0.9925 0.8607
2.250 0.1236 0.02801 0.01880 -0.0008 0.9683 0.8615
2.500 0.1801 0.02778 0.01876 -0.0060 0.9386 0.8625
2.750 0.2307 0.02710 0.01828 -0.0093 0.9036 0.8636
3.000 0.2668 0.02620 0.01759 -0.0098 0.8571 0.8647
3.250 0.2944 0.02542 0.01701 -0.0087 0.7919 0.8657
3.750 0.4151 0.02567 0.01500 -0.0148 0.3268 0.8666
4.000 0.4385 0.02669 0.01551 -0.0146 0.2479 0.8680
4.250 0.4658 0.02766 0.01613 -0.0151 0.2002 0.8691
4.500 0.4962 0.02858 0.01689 -0.0161 0.1693 0.8699
4.750 0.5283 0.02951 0.01770 -0.0173 0.1483 0.8708
5.000 0.5626 0.03045 0.01861 -0.0187 0.1325 0.8719
5.250 0.5976 0.03147 0.01969 -0.0202 0.1207 0.8731
5.500 0.6315 0.03262 0.02079 -0.0216 0.1119 0.8740
5.750 0.6646 0.03380 0.02211 -0.0228 0.1041 0.8747
6.000 0.6954 0.03511 0.02342 -0.0237 0.0982 0.8753
6.250 0.7257 0.03657 0.02515 -0.0243 0.0931 0.8760
6.500 0.7529 0.03789 0.02651 -0.0247 0.0888 0.8770
6.750 0.7791 0.03960 0.02849 -0.0248 0.0850 0.8781
7.000 0.8040 0.04162 0.03089 -0.0246 0.0821 0.8792
7.250 0.8273 0.04349 0.03301 -0.0245 0.0792 0.8803
7.500 0.8507 0.04519 0.03480 -0.0246 0.0766 0.8812
7.750 0.8684 0.04783 0.03790 -0.0239 0.0743 0.8819
8.000 0.8824 0.05093 0.04154 -0.0229 0.0729 0.8825
8.250 0.8933 0.05427 0.04536 -0.0218 0.0718 0.8831
8.500 0.9009 0.05766 0.04920 -0.0207 0.0706 0.8839
8.750 0.9063 0.06103 0.05293 -0.0196 0.0694 0.8848
9.000 0.9111 0.06423 0.05643 -0.0188 0.0681 0.8858
9.250 0.9180 0.06712 0.05949 -0.0182 0.0670 0.8868
9.500 0.9289 0.06982 0.06225 -0.0180 0.0660 0.8877
9.750 0.9178 0.07429 0.06704 -0.0171 0.0658 0.8885
10.000 0.9004 0.07890 0.07193 -0.0162 0.0658 0.8891
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Polar data table (+)
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