AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 200,000 Max Cl/Cd: 71.7 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83150q-il-200000-n5.txt Download as CSV file: xf-ah83150q-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-150 Q
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2338 0.10506 0.10048 -0.0544 0.7340 0.0246
-10.250 -0.2404 0.09978 0.09523 -0.0595 0.7320 0.0254
-10.000 -0.2431 0.09491 0.09041 -0.0636 0.7298 0.0255
-9.750 -0.2246 0.09404 0.08953 -0.0599 0.7274 0.0272
-9.500 -0.2229 0.09017 0.08568 -0.0620 0.7252 0.0271
-9.250 -0.2216 0.08633 0.08185 -0.0643 0.7230 0.0271
-9.000 -0.2183 0.08311 0.07863 -0.0659 0.7209 0.0285
-8.750 -0.2191 0.07907 0.07460 -0.0687 0.7189 0.0292
-8.500 -0.2252 0.07401 0.06954 -0.0730 0.7168 0.0297
-8.250 -0.2326 0.06943 0.06498 -0.0766 0.7142 0.0297
-7.250 -0.2718 0.05513 0.04973 -0.0776 0.7048 0.0318
-6.750 -0.2591 0.04161 0.03572 -0.0754 0.7016 0.0161
-6.500 -0.2449 0.03940 0.03342 -0.0750 0.6993 0.0158
-6.250 -0.2303 0.03689 0.03071 -0.0743 0.6968 0.0153
-6.000 -0.2145 0.03410 0.02761 -0.0734 0.6945 0.0147
-5.750 -0.1969 0.03102 0.02411 -0.0722 0.6925 0.0139
-5.250 -0.1528 0.02603 0.01806 -0.0698 0.6887 0.0127
-5.000 -0.1285 0.02449 0.01627 -0.0694 0.6869 0.0126
-4.750 -0.1032 0.02313 0.01463 -0.0689 0.6851 0.0126
-4.500 -0.0771 0.02194 0.01327 -0.0686 0.6827 0.0127
-4.250 -0.0508 0.02091 0.01209 -0.0683 0.6805 0.0127
-4.000 -0.0249 0.01991 0.01101 -0.0681 0.6782 0.0129
-3.750 0.0007 0.01905 0.01011 -0.0678 0.6760 0.0133
-3.500 0.0261 0.01836 0.00938 -0.0674 0.6739 0.0137
-3.250 0.0516 0.01776 0.00873 -0.0671 0.6721 0.0143
-3.000 0.0772 0.01727 0.00818 -0.0668 0.6705 0.0150
-2.750 0.1027 0.01686 0.00774 -0.0666 0.6685 0.0172
-2.500 0.1283 0.01653 0.00741 -0.0665 0.6658 0.0190
-2.250 0.1544 0.01621 0.00703 -0.0663 0.6632 0.0205
-2.000 0.1807 0.01591 0.00669 -0.0662 0.6610 0.0226
-1.750 0.2073 0.01564 0.00638 -0.0660 0.6589 0.0279
-1.500 0.2306 0.01477 0.00606 -0.0658 0.6570 0.1599
-1.250 0.2310 0.01320 0.00684 -0.0600 0.6552 0.7426
-1.000 0.2491 0.01420 0.00781 -0.0564 0.6533 0.8307
-0.750 0.2620 0.01482 0.00847 -0.0517 0.6504 0.8607
-0.500 0.2822 0.01500 0.00860 -0.0496 0.6476 0.8745
-0.250 0.3071 0.01498 0.00851 -0.0487 0.6450 0.8788
0.000 0.3344 0.01495 0.00836 -0.0488 0.6427 0.8813
0.250 0.3625 0.01490 0.00820 -0.0490 0.6406 0.8835
0.500 0.3912 0.01487 0.00804 -0.0494 0.6387 0.8855
0.750 0.4175 0.01494 0.00811 -0.0496 0.6351 0.8877
1.000 0.4445 0.01496 0.00810 -0.0498 0.6318 0.8893
1.250 0.4719 0.01494 0.00802 -0.0500 0.6289 0.8905
1.500 0.4997 0.01490 0.00792 -0.0502 0.6264 0.8919
1.750 0.5283 0.01486 0.00781 -0.0505 0.6242 0.8932
2.000 0.5552 0.01491 0.00786 -0.0507 0.6210 0.8945
2.250 0.5815 0.01498 0.00794 -0.0508 0.6170 0.8959
2.500 0.6089 0.01498 0.00794 -0.0510 0.6136 0.8976
2.750 0.6376 0.01495 0.00787 -0.0515 0.6108 0.8989
3.000 0.6673 0.01490 0.00777 -0.0520 0.6084 0.8999
3.250 0.6927 0.01504 0.00797 -0.0522 0.6035 0.9012
3.500 0.7202 0.01508 0.00803 -0.0525 0.5993 0.9025
3.750 0.7481 0.01502 0.00796 -0.0527 0.5958 0.9037
4.000 0.7763 0.01496 0.00789 -0.0530 0.5927 0.9048
4.250 0.8005 0.01509 0.00811 -0.0528 0.5870 0.9060
4.500 0.8277 0.01509 0.00814 -0.0530 0.5826 0.9070
4.750 0.8564 0.01502 0.00806 -0.0533 0.5791 0.9079
5.000 0.8807 0.01515 0.00828 -0.0532 0.5731 0.9094
5.250 0.9069 0.01517 0.00835 -0.0532 0.5679 0.9109
5.500 0.9357 0.01510 0.00828 -0.0536 0.5637 0.9122
5.750 0.9590 0.01528 0.00858 -0.0533 0.5563 0.9136
6.000 0.9865 0.01526 0.00857 -0.0536 0.5505 0.9147
6.250 1.0109 0.01538 0.00879 -0.0535 0.5427 0.9159
6.750 1.0598 0.01536 0.00881 -0.0529 0.5211 0.9184
7.000 1.0810 0.01543 0.00892 -0.0520 0.5075 0.9202
7.250 1.1026 0.01557 0.00911 -0.0513 0.4956 0.9221
7.500 1.1242 0.01575 0.00931 -0.0507 0.4839 0.9237
7.750 1.1450 0.01597 0.00956 -0.0500 0.4714 0.9255
8.000 1.1639 0.01625 0.00984 -0.0490 0.4570 0.9274
8.250 1.1809 0.01660 0.01020 -0.0478 0.4420 0.9295
8.500 1.1938 0.01701 0.01060 -0.0459 0.4269 0.9319
8.750 1.2035 0.01754 0.01113 -0.0436 0.4109 0.9352
9.000 1.2124 0.01822 0.01181 -0.0415 0.3947 0.9395
9.250 1.2212 0.01905 0.01263 -0.0397 0.3784 0.9442
9.500 1.2302 0.02003 0.01361 -0.0383 0.3616 0.9494
9.750 1.2391 0.02120 0.01477 -0.0373 0.3437 0.9570
10.000 1.2462 0.02259 0.01614 -0.0365 0.3232 0.9817
10.250 1.2487 0.02423 0.01771 -0.0351 0.3012 1.0000
10.500 1.2494 0.02609 0.01946 -0.0338 0.2795 1.0000
10.750 1.2514 0.02794 0.02125 -0.0326 0.2577 1.0000
11.000 1.2527 0.02989 0.02312 -0.0315 0.2380 1.0000
11.250 1.2555 0.03178 0.02496 -0.0305 0.2208 1.0000
11.500 1.2584 0.03370 0.02685 -0.0296 0.2038 1.0000
11.750 1.2616 0.03565 0.02876 -0.0288 0.1886 1.0000
12.000 1.2646 0.03765 0.03074 -0.0281 0.1743 1.0000
12.250 1.2683 0.03967 0.03275 -0.0275 0.1624 1.0000
12.500 1.2720 0.04175 0.03481 -0.0269 0.1513 1.0000
12.750 1.2776 0.04373 0.03681 -0.0265 0.1408 1.0000
13.000 1.2825 0.04580 0.03891 -0.0261 0.1321 1.0000
13.250 1.2865 0.04803 0.04116 -0.0258 0.1240 1.0000
13.500 1.2928 0.05006 0.04326 -0.0256 0.1160 1.0000
13.750 1.2965 0.05242 0.04563 -0.0254 0.1087 1.0000
14.000 1.3017 0.05468 0.04795 -0.0254 0.1007 1.0000
14.250 1.3058 0.05708 0.05041 -0.0253 0.0935 1.0000
14.500 1.3084 0.05970 0.05305 -0.0254 0.0861 1.0000
14.750 1.3126 0.06221 0.05563 -0.0255 0.0793 1.0000
15.000 1.3133 0.06518 0.05863 -0.0257 0.0735 1.0000
15.250 1.3170 0.06783 0.06137 -0.0260 0.0678 1.0000
15.500 1.3171 0.07099 0.06457 -0.0264 0.0635 1.0000
15.750 1.3195 0.07390 0.06758 -0.0268 0.0597 1.0000
16.000 1.3198 0.07716 0.07089 -0.0274 0.0552 1.0000
16.250 1.3181 0.08074 0.07450 -0.0281 0.0522 1.0000
16.500 1.3209 0.08374 0.07764 -0.0287 0.0488 1.0000
16.750 1.3200 0.08731 0.08127 -0.0296 0.0457 1.0000
17.000 1.3166 0.09132 0.08533 -0.0307 0.0435 1.0000
17.250 1.3187 0.09457 0.08872 -0.0317 0.0414 1.0000
17.500 1.3192 0.09810 0.09238 -0.0328 0.0391 1.0000
17.750 1.3170 0.10210 0.09646 -0.0342 0.0369 1.0000
18.000 1.3121 0.10656 0.10097 -0.0358 0.0351 1.0000
18.250 1.3138 0.11004 0.10462 -0.0371 0.0330 1.0000
18.500 1.3128 0.11399 0.10869 -0.0387 0.0311 1.0000
18.750 1.3090 0.11847 0.11327 -0.0406 0.0294 1.0000
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Polar data table (+)
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