ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: ONERA HOR20 AIRFOIL (hor20-il) Reynolds number: 100,000 Max Cl/Cd: 44.88 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor20-il-100000-n5.txt Download as CSV file: xf-hor20-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR20 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5676 0.08999 0.08353 -0.0424 1.0000 0.1146
-12.000 -0.7950 0.05283 0.04566 -0.0674 1.0000 0.1227
-11.750 -0.8144 0.04749 0.04021 -0.0714 1.0000 0.1246
-11.500 -0.8054 0.04588 0.03867 -0.0721 1.0000 0.1265
-11.250 -0.8179 0.04237 0.03509 -0.0743 1.0000 0.1284
-11.000 -0.8271 0.03960 0.03219 -0.0750 1.0000 0.1305
-10.750 -0.8350 0.03734 0.02976 -0.0743 1.0000 0.1328
-10.500 -0.8148 0.03612 0.02852 -0.0755 0.9894 0.1353
-10.250 -0.7818 0.03508 0.02750 -0.0783 0.9735 0.1385
-10.000 -0.7523 0.03340 0.02561 -0.0815 0.9582 0.1427
-9.750 -0.7220 0.03225 0.02437 -0.0837 0.9426 0.1462
-9.500 -0.6932 0.03150 0.02361 -0.0849 0.9250 0.1494
-9.250 -0.6681 0.03044 0.02240 -0.0857 0.9075 0.1532
-9.000 -0.6443 0.02943 0.02122 -0.0861 0.8907 0.1569
-8.750 -0.6190 0.02894 0.02074 -0.0860 0.8748 0.1601
-8.500 -0.5949 0.02826 0.01994 -0.0858 0.8602 0.1642
-8.250 -0.5721 0.02743 0.01891 -0.0857 0.8447 0.1687
-8.000 -0.5471 0.02707 0.01858 -0.0852 0.8312 0.1723
-7.750 -0.5225 0.02657 0.01798 -0.0849 0.8177 0.1769
-7.500 -0.4977 0.02593 0.01715 -0.0848 0.8050 0.1822
-7.250 -0.4720 0.02566 0.01688 -0.0844 0.7928 0.1862
-7.000 -0.4460 0.02524 0.01636 -0.0842 0.7808 0.1916
-6.750 -0.4200 0.02477 0.01574 -0.0841 0.7690 0.1970
-6.500 -0.3931 0.02453 0.01550 -0.0838 0.7581 0.2016
-6.250 -0.3660 0.02415 0.01499 -0.0838 0.7464 0.2075
-6.000 -0.3390 0.02381 0.01452 -0.0837 0.7365 0.2128
-5.750 -0.3113 0.02359 0.01432 -0.0836 0.7249 0.2180
-5.500 -0.2838 0.02326 0.01379 -0.0835 0.7155 0.2245
-5.250 -0.2559 0.02299 0.01350 -0.0835 0.7048 0.2299
-5.000 -0.2281 0.02279 0.01326 -0.0834 0.6947 0.2356
-4.750 -0.1998 0.02250 0.01278 -0.0834 0.6859 0.2425
-4.500 -0.1716 0.02228 0.01259 -0.0835 0.6754 0.2480
-4.250 -0.1434 0.02211 0.01235 -0.0833 0.6669 0.2541
-4.000 -0.1146 0.02188 0.01196 -0.0835 0.6577 0.2614
-3.750 -0.0862 0.02170 0.01182 -0.0834 0.6484 0.2670
-3.500 -0.0578 0.02156 0.01161 -0.0833 0.6410 0.2735
-3.250 -0.0285 0.02139 0.01132 -0.0836 0.6319 0.2810
-3.000 -0.0001 0.02126 0.01125 -0.0835 0.6234 0.2867
-2.750 0.0287 0.02117 0.01107 -0.0834 0.6167 0.2935
-2.500 0.0581 0.02105 0.01087 -0.0836 0.6080 0.3012
-2.250 0.0867 0.02098 0.01087 -0.0836 0.6003 0.3071
-2.000 0.1157 0.02093 0.01073 -0.0835 0.5939 0.3143
-1.750 0.1451 0.02086 0.01060 -0.0837 0.5859 0.3222
-1.500 0.1738 0.02084 0.01064 -0.0837 0.5785 0.3283
-1.250 0.2029 0.02082 0.01054 -0.0836 0.5724 0.3359
-1.000 0.2322 0.02079 0.01046 -0.0838 0.5656 0.3439
-0.750 0.2609 0.02082 0.01055 -0.0837 0.5582 0.3507
-0.500 0.2901 0.02083 0.01049 -0.0837 0.5518 0.3593
-0.250 0.3193 0.02085 0.01044 -0.0837 0.5461 0.3674
0.000 0.3479 0.02093 0.01061 -0.0837 0.5388 0.3753
0.250 0.3771 0.02097 0.01056 -0.0838 0.5321 0.3854
0.500 0.4058 0.02102 0.01061 -0.0836 0.5265 0.3930
0.750 0.4345 0.02114 0.01074 -0.0837 0.5201 0.4025
1.000 0.4632 0.02122 0.01083 -0.0837 0.5132 0.4118
1.250 0.4917 0.02132 0.01092 -0.0835 0.5074 0.4207
1.500 0.5211 0.02144 0.01090 -0.0836 0.5022 0.4315
1.750 0.5487 0.02158 0.01118 -0.0834 0.4954 0.4395
2.000 0.5771 0.02172 0.01131 -0.0833 0.4891 0.4498
2.250 0.6058 0.02182 0.01136 -0.0832 0.4839 0.4590
2.500 0.6338 0.02199 0.01155 -0.0831 0.4783 0.4680
2.750 0.6617 0.02219 0.01177 -0.0831 0.4717 0.4783
3.000 0.6892 0.02231 0.01195 -0.0828 0.4660 0.4866
3.250 0.7177 0.02245 0.01200 -0.0827 0.4611 0.4967
3.500 0.7447 0.02265 0.01229 -0.0825 0.4550 0.5053
3.750 0.7716 0.02283 0.01253 -0.0822 0.4487 0.5145
4.000 0.7995 0.02299 0.01264 -0.0821 0.4434 0.5245
4.250 0.8271 0.02310 0.01274 -0.0818 0.4388 0.5336
4.500 0.8528 0.02338 0.01313 -0.0815 0.4322 0.5436
4.750 0.8790 0.02356 0.01338 -0.0811 0.4263 0.5528
5.000 0.9064 0.02371 0.01350 -0.0808 0.4214 0.5635
5.250 0.9328 0.02394 0.01377 -0.0805 0.4161 0.5742
5.500 0.9576 0.02423 0.01418 -0.0800 0.4096 0.5868
5.750 0.9834 0.02440 0.01441 -0.0795 0.4039 0.6009
6.000 1.0105 0.02454 0.01452 -0.0792 0.3993 0.6177
6.250 1.0332 0.02489 0.01508 -0.0785 0.3928 0.6351
6.500 1.0569 0.02513 0.01545 -0.0777 0.3868 0.6555
6.750 1.0815 0.02526 0.01566 -0.0770 0.3818 0.6827
7.000 1.1034 0.02544 0.01604 -0.0758 0.3765 0.7276
7.250 1.1212 0.02538 0.01643 -0.0738 0.3704 1.0000
7.500 1.1457 0.02579 0.01678 -0.0734 0.3650 1.0000
7.750 1.1723 0.02612 0.01695 -0.0732 0.3605 1.0000
8.000 1.1913 0.02682 0.01775 -0.0722 0.3543 1.0000
8.250 1.2124 0.02736 0.01829 -0.0713 0.3486 1.0000
8.500 1.2356 0.02775 0.01860 -0.0706 0.3437 1.0000
8.750 1.2546 0.02840 0.01926 -0.0696 0.3382 1.0000
9.000 1.2714 0.02910 0.02002 -0.0682 0.3322 1.0000
9.250 1.2906 0.02964 0.02052 -0.0671 0.3272 1.0000
9.500 1.3107 0.03017 0.02098 -0.0661 0.3226 1.0000
9.750 1.3209 0.03114 0.02208 -0.0641 0.3169 1.0000
10.000 1.3324 0.03191 0.02288 -0.0621 0.3119 1.0000
10.250 1.3489 0.03250 0.02340 -0.0607 0.3075 1.0000
10.500 1.3574 0.03358 0.02454 -0.0587 0.3028 1.0000
10.750 1.3626 0.03488 0.02594 -0.0567 0.2975 1.0000
11.000 1.3734 0.03590 0.02697 -0.0552 0.2927 1.0000
11.250 1.3904 0.03660 0.02758 -0.0542 0.2886 1.0000
11.500 1.3875 0.03869 0.02985 -0.0524 0.2833 1.0000
11.750 1.3919 0.04036 0.03159 -0.0511 0.2783 1.0000
12.000 1.4045 0.04143 0.03263 -0.0501 0.2741 1.0000
12.250 1.4089 0.04327 0.03451 -0.0491 0.2696 1.0000
12.500 1.4041 0.04598 0.03738 -0.0481 0.2646 1.0000
12.750 1.4092 0.04786 0.03929 -0.0473 0.2602 1.0000
13.000 1.4265 0.04861 0.03995 -0.0466 0.2565 1.0000
13.250 1.4124 0.05251 0.04405 -0.0461 0.2516 1.0000
13.500 1.4051 0.05587 0.04753 -0.0458 0.2468 1.0000
13.750 1.4128 0.05763 0.04929 -0.0453 0.2429 1.0000
14.000 1.4237 0.05908 0.05071 -0.0447 0.2393 1.0000
14.250 1.3908 0.06564 0.05754 -0.0455 0.2339 1.0000
14.500 1.3856 0.06912 0.06109 -0.0456 0.2295 1.0000
14.750 1.4032 0.06977 0.06168 -0.0450 0.2263 1.0000
15.000 1.3678 0.07737 0.06951 -0.0466 0.2211 1.0000
15.250 1.3353 0.08502 0.07734 -0.0486 0.2154 1.0000
15.500 1.3543 0.08543 0.07771 -0.0479 0.2125 1.0000
15.750 1.3860 0.08405 0.07622 -0.0465 0.2104 1.0000
16.000 1.2565 0.10694 0.09961 -0.0552 0.1992 1.0000
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