AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 500,000 Max Cl/Cd: 111.5 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-7-il-500000.txt Download as CSV file: xf-ah21-7-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5192 0.08588 0.08371 -0.0281 1.0000 0.0227
-8.500 -0.5325 0.08237 0.08025 -0.0281 1.0000 0.0233
-8.250 -0.5517 0.07913 0.07705 -0.0274 1.0000 0.0233
-8.000 -0.5700 0.07481 0.07276 -0.0298 0.9992 0.0231
-7.750 -0.5543 0.05887 0.05645 -0.0500 0.9933 0.0253
-7.500 -0.5461 0.05242 0.04961 -0.0545 0.9884 0.0255
-7.250 -0.5430 0.04328 0.04023 -0.0587 0.9853 0.0266
-7.000 -0.5176 0.04153 0.03844 -0.0608 0.9840 0.0275
-6.750 -0.5011 0.03978 0.03661 -0.0606 0.9799 0.0290
-6.500 -0.4719 0.03896 0.03529 -0.0610 0.9766 0.0331
-6.250 -0.4618 0.02676 0.02217 -0.0618 0.9739 0.0245
-6.000 -0.4371 0.02194 0.01674 -0.0622 0.9727 0.0223
-5.750 -0.4066 0.01994 0.01442 -0.0631 0.9719 0.0225
-5.500 -0.3821 0.01877 0.01306 -0.0626 0.9690 0.0233
-5.250 -0.3577 0.01746 0.01155 -0.0619 0.9660 0.0235
-5.000 -0.3288 0.01638 0.01033 -0.0622 0.9639 0.0239
-4.750 -0.2983 0.01554 0.00938 -0.0629 0.9622 0.0244
-4.500 -0.2663 0.01482 0.00858 -0.0638 0.9608 0.0249
-4.250 -0.2329 0.01430 0.00800 -0.0650 0.9596 0.0256
-4.000 -0.2007 0.01328 0.00693 -0.0662 0.9587 0.0278
-3.750 -0.1736 0.01287 0.00649 -0.0662 0.9558 0.0292
-3.500 -0.1490 0.01251 0.00611 -0.0655 0.9516 0.0309
-3.250 -0.1173 0.01219 0.00574 -0.0664 0.9493 0.0330
-3.000 -0.0838 0.01174 0.00529 -0.0676 0.9476 0.0401
-2.750 -0.0501 0.01109 0.00493 -0.0690 0.9463 0.1017
-2.500 -0.0159 0.01049 0.00472 -0.0708 0.9451 0.2057
-2.250 0.0191 0.00992 0.00457 -0.0727 0.9442 0.3265
-2.000 0.0362 0.00950 0.00452 -0.0707 0.9375 0.4330
-1.750 0.0668 0.00891 0.00444 -0.0715 0.9350 0.5770
-1.500 0.0990 0.00843 0.00437 -0.0723 0.9332 0.6963
-1.250 0.1335 0.00810 0.00428 -0.0734 0.9318 0.7696
-1.000 0.1698 0.00784 0.00415 -0.0748 0.9308 0.8206
-0.750 0.1883 0.00773 0.00414 -0.0723 0.9239 0.8613
-0.500 0.2209 0.00752 0.00398 -0.0728 0.9212 0.8910
-0.250 0.2572 0.00729 0.00378 -0.0742 0.9192 0.9150
0.000 0.2954 0.00705 0.00355 -0.0758 0.9174 0.9332
0.250 0.3233 0.00689 0.00341 -0.0753 0.9113 0.9515
0.500 0.3611 0.00670 0.00322 -0.0771 0.9067 0.9644
0.750 0.4052 0.00646 0.00296 -0.0802 0.9029 0.9727
1.000 0.4446 0.00635 0.00285 -0.0824 0.8944 0.9805
1.250 0.4891 0.00617 0.00266 -0.0857 0.8871 0.9845
1.500 0.5319 0.00606 0.00254 -0.0888 0.8748 0.9881
1.750 0.5734 0.00597 0.00243 -0.0916 0.8595 0.9922
2.000 0.6132 0.00593 0.00235 -0.0940 0.8368 0.9968
2.250 0.6520 0.00593 0.00226 -0.0963 0.8052 1.0000
2.500 0.6712 0.00602 0.00219 -0.0943 0.7635 1.0000
2.750 0.6848 0.00625 0.00220 -0.0911 0.7132 1.0000
3.000 0.6937 0.00659 0.00227 -0.0870 0.6530 1.0000
3.250 0.7009 0.00703 0.00239 -0.0826 0.5848 1.0000
3.500 0.7104 0.00758 0.00258 -0.0788 0.5097 1.0000
3.750 0.7231 0.00818 0.00282 -0.0758 0.4313 1.0000
4.000 0.7386 0.00880 0.00310 -0.0735 0.3548 1.0000
4.250 0.7564 0.00941 0.00338 -0.0717 0.2877 1.0000
4.500 0.7755 0.00999 0.00367 -0.0702 0.2295 1.0000
4.750 0.7958 0.01052 0.00398 -0.0689 0.1813 1.0000
5.000 0.8168 0.01102 0.00431 -0.0678 0.1446 1.0000
5.250 0.8383 0.01151 0.00464 -0.0667 0.1158 1.0000
5.500 0.8603 0.01195 0.00498 -0.0657 0.0946 1.0000
5.750 0.8823 0.01240 0.00536 -0.0646 0.0796 1.0000
6.000 0.9044 0.01284 0.00576 -0.0636 0.0687 1.0000
6.250 0.9259 0.01334 0.00624 -0.0625 0.0600 1.0000
6.500 0.9481 0.01376 0.00665 -0.0615 0.0538 1.0000
6.750 0.9686 0.01434 0.00725 -0.0602 0.0488 1.0000
7.000 0.9909 0.01475 0.00770 -0.0592 0.0452 1.0000
7.250 1.0110 0.01535 0.00830 -0.0579 0.0413 1.0000
7.500 1.0303 0.01603 0.00904 -0.0564 0.0386 1.0000
7.750 1.0516 0.01651 0.00958 -0.0553 0.0364 1.0000
8.000 1.0723 0.01702 0.01013 -0.0541 0.0343 1.0000
8.250 1.0903 0.01780 0.01094 -0.0525 0.0320 1.0000
8.500 1.1068 0.01883 0.01206 -0.0507 0.0302 1.0000
8.750 1.1267 0.01937 0.01268 -0.0493 0.0290 1.0000
9.000 1.1458 0.01993 0.01331 -0.0479 0.0274 1.0000
9.250 1.1642 0.02049 0.01391 -0.0464 0.0260 1.0000
9.500 1.1801 0.02136 0.01483 -0.0446 0.0245 1.0000
9.750 1.1948 0.02292 0.01651 -0.0428 0.0232 1.0000
10.000 1.2125 0.02344 0.01713 -0.0412 0.0222 1.0000
10.250 1.2289 0.02410 0.01790 -0.0394 0.0211 1.0000
10.500 1.2443 0.02475 0.01861 -0.0377 0.0201 1.0000
10.750 1.2585 0.02546 0.01935 -0.0358 0.0191 1.0000
11.000 1.2663 0.02780 0.02184 -0.0333 0.0179 1.0000
11.250 1.2787 0.02874 0.02295 -0.0312 0.0174 1.0000
11.500 1.2905 0.02957 0.02392 -0.0290 0.0166 1.0000
11.750 1.3007 0.03057 0.02505 -0.0268 0.0158 1.0000
12.000 1.3103 0.03148 0.02605 -0.0246 0.0151 1.0000
12.250 1.3198 0.03228 0.02691 -0.0226 0.0145 1.0000
12.500 1.3246 0.03370 0.02839 -0.0203 0.0139 1.0000
12.750 1.3160 0.03709 0.03203 -0.0169 0.0133 1.0000
13.000 1.3188 0.03871 0.03384 -0.0147 0.0131 1.0000
13.250 1.3184 0.04074 0.03608 -0.0125 0.0128 1.0000
13.500 1.3162 0.04301 0.03855 -0.0105 0.0124 1.0000
13.750 1.3115 0.04565 0.04139 -0.0088 0.0122 1.0000
14.000 1.3046 0.04863 0.04456 -0.0074 0.0119 1.0000
14.250 1.2969 0.05185 0.04795 -0.0067 0.0116 1.0000
14.500 1.2845 0.05596 0.05226 -0.0065 0.0115 1.0000
14.750 1.2729 0.06025 0.05672 -0.0071 0.0113 1.0000
15.000 1.2580 0.06548 0.06213 -0.0087 0.0112 1.0000
15.250 1.2352 0.07260 0.06948 -0.0119 0.0113 1.0000
15.500 1.2163 0.07988 0.07693 -0.0160 0.0112 1.0000
15.750 1.1836 0.09092 0.08823 -0.0228 0.0114 1.0000
16.000 1.1382 0.10633 0.10390 -0.0329 0.0118 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH21 7% version (Andrew Hollom) (ah21-7-il)