FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il) Reynolds number: 100,000 Max Cl/Cd: 45.26 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k153-il-100000.txt Download as CSV file: xf-fx62k153-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 62-K-153/20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3151 0.10664 0.10286 -0.0498 0.9678 0.1156
-8.250 -0.3430 0.10334 0.09964 -0.0512 0.9670 0.1186
-8.000 -0.4086 0.10235 0.09834 -0.0541 0.9743 0.1115
-7.750 -0.4223 0.09965 0.09569 -0.0537 0.9712 0.1146
-7.500 -0.4491 0.09687 0.09299 -0.0532 0.9686 0.1163
-7.250 -0.4792 0.09305 0.08921 -0.0551 0.9658 0.1172
-7.000 -0.5154 0.08841 0.08445 -0.0605 0.9649 0.1188
-6.750 -0.5148 0.08356 0.07961 -0.0618 0.9629 0.1225
-6.500 -0.5000 0.08078 0.07684 -0.0620 0.9607 0.1297
-6.250 -0.5124 0.07596 0.07181 -0.0658 0.9609 0.1373
-6.000 -0.5070 0.07368 0.06959 -0.0635 0.9588 0.1432
-5.750 -0.6092 0.07675 0.07295 -0.0389 1.0001 0.1261
-5.500 -0.6018 0.07166 0.06761 -0.0438 1.0001 0.1378
-5.250 -0.5886 0.06778 0.06353 -0.0469 1.0001 0.1521
-5.000 -0.5741 0.06446 0.06015 -0.0483 1.0001 0.1676
-4.750 -0.3249 0.04319 0.03541 -0.0906 0.9444 0.0674
-4.500 -0.2942 0.04130 0.03314 -0.0918 0.9417 0.0693
-4.250 -0.2557 0.03943 0.03086 -0.0937 0.9378 0.0700
-4.000 -0.2040 0.03857 0.02955 -0.0977 0.9325 0.0759
-3.750 -0.1855 0.03719 0.02822 -0.0964 0.9290 0.0787
-3.500 -0.1585 0.03646 0.02755 -0.0966 0.9256 0.0843
-3.250 -0.1179 0.03576 0.02694 -0.0993 0.9213 0.0976
-3.000 -0.0752 0.03506 0.02640 -0.1026 0.9165 0.1240
-2.750 -0.0422 0.03430 0.02831 -0.1032 0.9123 0.6540
-2.500 -0.0413 0.03605 0.02999 -0.0958 0.9082 0.6936
-2.250 -0.0335 0.03769 0.03155 -0.0891 0.9037 0.7241
-2.000 -0.0412 0.03841 0.03226 -0.0818 0.8989 0.7428
-1.750 -0.0398 0.03924 0.03303 -0.0752 0.8944 0.7670
-1.500 -0.0303 0.04013 0.03385 -0.0688 0.8898 0.7964
-1.250 -0.0429 0.04021 0.03394 -0.0611 0.8844 0.8145
-1.000 -0.0419 0.04039 0.03407 -0.0548 0.8796 0.8396
-0.750 -0.0309 0.04049 0.03405 -0.0504 0.8733 0.8615
-0.500 -0.0192 0.04048 0.03395 -0.0485 0.8670 0.8711
-0.250 0.0275 0.04089 0.03413 -0.0525 0.8598 0.8772
0.000 0.0409 0.04098 0.03414 -0.0516 0.8522 0.8823
0.250 0.0879 0.04130 0.03427 -0.0552 0.8461 0.8872
0.500 0.1010 0.04153 0.03444 -0.0546 0.8370 0.8919
0.750 0.1497 0.04186 0.03461 -0.0587 0.8315 0.8960
1.000 0.1581 0.04204 0.03476 -0.0569 0.8218 0.9004
1.250 0.2068 0.04236 0.03495 -0.0609 0.8167 0.9046
1.500 0.2215 0.04282 0.03539 -0.0606 0.8066 0.9084
1.750 0.2635 0.04296 0.03544 -0.0632 0.8020 0.9123
2.000 0.2728 0.04346 0.03594 -0.0619 0.7920 0.9163
2.250 0.3182 0.04375 0.03616 -0.0654 0.7876 0.9199
2.500 0.3315 0.04435 0.03677 -0.0648 0.7773 0.9237
2.750 0.3725 0.04450 0.03687 -0.0673 0.7729 0.9273
3.000 0.3838 0.04528 0.03768 -0.0665 0.7629 0.9312
3.250 0.4271 0.04549 0.03787 -0.0696 0.7585 0.9350
3.500 0.4395 0.04619 0.03860 -0.0688 0.7480 0.9389
3.750 0.4804 0.04626 0.03868 -0.0712 0.7438 0.9427
4.000 0.4945 0.04705 0.03952 -0.0707 0.7330 0.9471
4.250 0.5401 0.04682 0.03930 -0.0734 0.7289 0.9513
4.500 0.5543 0.04743 0.03997 -0.0728 0.7173 0.9558
4.750 0.6019 0.04703 0.03962 -0.0755 0.7139 0.9606
5.000 0.6144 0.04774 0.04040 -0.0748 0.7020 0.9662
5.250 0.6334 0.04838 0.04111 -0.0748 0.6916 0.9722
5.500 0.6773 0.04785 0.04067 -0.0771 0.6869 0.9786
5.750 0.6957 0.04843 0.04134 -0.0770 0.6752 0.9912
6.000 0.7486 0.04741 0.04042 -0.0802 0.6716 0.9999
6.250 0.7700 0.04818 0.04131 -0.0808 0.6595 0.9999
6.500 0.8242 0.04704 0.04030 -0.0840 0.6569 0.9999
6.750 0.8430 0.04801 0.04139 -0.0844 0.6445 0.9999
7.000 0.8662 0.04875 0.04227 -0.0851 0.6332 0.9999
7.250 0.9197 0.04713 0.04083 -0.0878 0.6295 0.9999
7.500 0.9477 0.04710 0.04094 -0.0883 0.6176 0.9999
7.750 1.0175 0.04297 0.03705 -0.0910 0.6149 0.9999
8.000 1.0896 0.03804 0.03236 -0.0934 0.6135 0.9999
8.250 1.1258 0.03642 0.03096 -0.0936 0.6008 0.9999
8.500 1.1710 0.03400 0.02875 -0.0944 0.5883 0.9999
8.750 1.2225 0.03121 0.02616 -0.0957 0.5732 0.9999
9.000 1.2621 0.02965 0.02477 -0.0962 0.5504 0.9999
9.250 1.2912 0.02902 0.02421 -0.0958 0.5188 0.9999
9.500 1.3124 0.02900 0.02412 -0.0947 0.4761 0.9999
9.750 1.3215 0.02999 0.02490 -0.0925 0.4251 0.9999
10.000 1.3210 0.03182 0.02643 -0.0898 0.3680 0.9999
10.250 1.3135 0.03435 0.02856 -0.0867 0.3098 0.9999
10.500 1.3039 0.03727 0.03105 -0.0838 0.2596 0.9999
10.750 1.2962 0.04027 0.03373 -0.0813 0.2174 0.9999
11.000 1.2923 0.04313 0.03633 -0.0792 0.1844 0.9999
11.250 1.2915 0.04583 0.03878 -0.0775 0.1602 0.9999
11.500 1.2958 0.04822 0.04104 -0.0761 0.1399 0.9999
11.750 1.3040 0.05038 0.04310 -0.0748 0.1240 0.9999
12.000 1.3155 0.05237 0.04503 -0.0737 0.1107 0.9999
12.250 1.3302 0.05422 0.04684 -0.0728 0.0996 0.9999
12.500 1.3563 0.05570 0.04819 -0.0723 0.0896 0.9999
12.750 1.3679 0.05780 0.05047 -0.0715 0.0821 0.9999
13.000 1.3771 0.06015 0.05294 -0.0708 0.0744 0.9999
13.250 1.3789 0.06254 0.05530 -0.0701 0.0674 0.9999
13.500 1.3750 0.06556 0.05860 -0.0691 0.0613 0.9999
13.750 1.3803 0.06816 0.06106 -0.0685 0.0540 0.9999
14.000 1.3765 0.07157 0.06489 -0.0674 0.0493 0.9999
14.250 1.3861 0.07467 0.06790 -0.0664 0.0428 0.9999
14.500 1.3796 0.07861 0.07228 -0.0654 0.0397 0.9999
14.750 1.3756 0.08220 0.07607 -0.0648 0.0368 0.9999
15.000 1.3832 0.08570 0.07947 -0.0643 0.0335 0.9999
15.250 1.3699 0.09016 0.08432 -0.0641 0.0327 0.9999
15.500 1.3572 0.09505 0.08957 -0.0643 0.0320 0.9999
15.750 1.3433 0.10033 0.09519 -0.0649 0.0314 0.9999
16.000 1.3275 0.10609 0.10127 -0.0662 0.0308 0.9999
16.250 1.3106 0.11232 0.10780 -0.0681 0.0307 0.9999
16.500 1.2910 0.11928 0.11505 -0.0710 0.0305 0.9999
16.750 1.2713 0.12669 0.12272 -0.0746 0.0308 0.9999
17.000 1.2502 0.13487 0.13116 -0.0793 0.0311 0.9999
17.250 1.2277 0.14400 0.14051 -0.0852 0.0315 0.9999
17.500 1.2066 0.15361 0.15029 -0.0917 0.0322 0.9999
17.750 1.1868 0.16365 0.16045 -0.0987 0.0329 0.9999
18.000 1.1688 0.17412 0.17100 -0.1060 0.0334 0.9999
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