AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 500,000 Max Cl/Cd: 127.51 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah63k127-il-500000.txt Download as CSV file: xf-ah63k127-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 63-K-127/24
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1261 0.08484 0.08177 -0.0858 0.7910 0.0160
-10.250 -0.1235 0.08130 0.07824 -0.0870 0.7901 0.0164
-10.000 -0.1216 0.07766 0.07461 -0.0883 0.7892 0.0166
-9.750 -0.1207 0.07387 0.07083 -0.0896 0.7884 0.0171
-9.500 -0.1203 0.07001 0.06699 -0.0910 0.7876 0.0173
-9.250 -0.1214 0.06596 0.06296 -0.0925 0.7867 0.0177
-9.000 -0.1239 0.06177 0.05878 -0.0942 0.7857 0.0184
-8.750 -0.1267 0.05769 0.05472 -0.0958 0.7846 0.0183
-8.500 -0.1324 0.05319 0.05024 -0.0980 0.7837 0.0186
-8.250 -0.1416 0.04844 0.04552 -0.1012 0.7825 0.0186
-8.000 -0.1595 0.04306 0.04016 -0.1056 0.7812 0.0183
-7.750 -0.1792 0.03947 0.03654 -0.1057 0.7793 0.0182
-7.500 -0.1882 0.03534 0.03232 -0.1059 0.7777 0.0187
-7.250 -0.1906 0.03148 0.02834 -0.1056 0.7760 0.0190
-7.000 -0.1854 0.02799 0.02462 -0.1050 0.7744 0.0204
-6.750 -0.1854 0.04113 0.03722 -0.1108 0.7760 0.0209
-6.500 -0.1732 0.03927 0.03503 -0.1094 0.7744 0.0213
-6.250 -0.1742 0.01599 0.01172 -0.1013 0.7702 0.0227
-6.000 -0.1574 0.01421 0.00990 -0.1009 0.7687 0.0237
-5.750 -0.1393 0.01264 0.00823 -0.1005 0.7668 0.0252
-5.500 -0.1195 0.01113 0.00651 -0.0999 0.7648 0.0277
-5.250 -0.0918 0.01201 0.00715 -0.0988 0.7627 0.0309
-4.500 -0.0245 0.01883 0.01255 -0.1025 0.7620 0.0191
-4.250 0.0008 0.01713 0.01064 -0.1017 0.7605 0.0172
-4.000 0.0260 0.01603 0.00941 -0.1011 0.7591 0.0164
-3.750 0.0508 0.01529 0.00858 -0.1005 0.7577 0.0165
-3.500 0.0755 0.01481 0.00803 -0.1000 0.7564 0.0169
-3.250 0.1004 0.01427 0.00748 -0.0996 0.7539 0.0181
-3.000 0.1261 0.01388 0.00706 -0.0993 0.7514 0.0203
-2.750 0.1521 0.01342 0.00652 -0.0991 0.7493 0.0250
-2.500 0.1767 0.01262 0.00609 -0.0988 0.7475 0.1245
-2.250 0.1996 0.01161 0.00585 -0.0987 0.7460 0.3487
-2.000 0.2184 0.01048 0.00581 -0.0976 0.7445 0.6670
-1.750 0.2427 0.01049 0.00601 -0.0965 0.7433 0.7579
-1.500 0.2665 0.01061 0.00621 -0.0955 0.7401 0.7954
-1.250 0.2926 0.01069 0.00628 -0.0950 0.7374 0.8108
-1.000 0.3195 0.01074 0.00629 -0.0947 0.7354 0.8227
-0.750 0.3457 0.01081 0.00633 -0.0941 0.7336 0.8360
-0.500 0.3727 0.01084 0.00632 -0.0938 0.7321 0.8457
-0.250 0.3998 0.01083 0.00627 -0.0935 0.7309 0.8521
0.000 0.4269 0.01086 0.00627 -0.0933 0.7292 0.8592
0.250 0.4514 0.01089 0.00633 -0.0927 0.7254 0.8655
0.500 0.4775 0.01087 0.00631 -0.0923 0.7228 0.8730
0.750 0.5037 0.01079 0.00623 -0.0919 0.7208 0.8795
1.000 0.5311 0.01068 0.00610 -0.0918 0.7192 0.8849
1.500 0.5883 0.01045 0.00581 -0.0922 0.7166 0.8929
1.750 0.6124 0.01046 0.00590 -0.0916 0.7117 0.8969
2.000 0.6404 0.01035 0.00579 -0.0918 0.7090 0.9008
2.250 0.6692 0.01020 0.00565 -0.0921 0.7069 0.9043
2.500 0.6971 0.01001 0.00546 -0.0921 0.7052 0.9078
2.750 0.7254 0.00983 0.00528 -0.0922 0.7037 0.9122
3.000 0.7505 0.00983 0.00535 -0.0919 0.6987 0.9171
3.250 0.7772 0.00966 0.00524 -0.0917 0.6954 0.9207
3.500 0.8054 0.00943 0.00503 -0.0918 0.6927 0.9244
3.750 0.8344 0.00919 0.00478 -0.0921 0.6896 0.9282
4.000 0.8600 0.00900 0.00467 -0.0917 0.6823 0.9323
4.250 0.8881 0.00870 0.00437 -0.0917 0.6775 0.9359
4.500 0.9131 0.00855 0.00431 -0.0912 0.6687 0.9408
4.750 0.9401 0.00839 0.00417 -0.0911 0.6614 0.9455
5.000 0.9656 0.00826 0.00407 -0.0906 0.6512 0.9504
5.250 0.9908 0.00818 0.00403 -0.0902 0.6380 0.9561
5.500 1.0166 0.00815 0.00401 -0.0899 0.6206 0.9622
5.750 1.0437 0.00822 0.00406 -0.0900 0.5991 0.9698
6.000 1.0736 0.00842 0.00421 -0.0908 0.5750 0.9785
6.250 1.1043 0.00870 0.00444 -0.0919 0.5495 0.9987
6.500 1.1233 0.00913 0.00477 -0.0906 0.5147 1.0000
6.750 1.1393 0.00972 0.00519 -0.0889 0.4724 1.0000
7.000 1.1493 0.01057 0.00578 -0.0862 0.4143 1.0000
7.250 1.1451 0.01199 0.00671 -0.0813 0.3232 1.0000
7.500 1.1312 0.01356 0.00780 -0.0747 0.2406 1.0000
7.750 1.1214 0.01510 0.00898 -0.0694 0.1789 1.0000
8.000 1.1191 0.01652 0.01018 -0.0657 0.1386 1.0000
8.250 1.1238 0.01780 0.01132 -0.0634 0.1127 1.0000
8.500 1.1310 0.01907 0.01249 -0.0616 0.0914 1.0000
8.750 1.1401 0.02021 0.01357 -0.0599 0.0731 1.0000
9.000 1.1485 0.02140 0.01466 -0.0582 0.0569 1.0000
9.250 1.1571 0.02258 0.01579 -0.0565 0.0434 1.0000
9.500 1.1643 0.02387 0.01703 -0.0546 0.0307 1.0000
9.750 1.1694 0.02533 0.01845 -0.0526 0.0211 1.0000
10.000 1.1731 0.02695 0.02008 -0.0504 0.0156 1.0000
10.250 1.1795 0.02839 0.02156 -0.0486 0.0128 1.0000
10.500 1.1780 0.03048 0.02375 -0.0461 0.0110 1.0000
10.750 1.1876 0.03177 0.02512 -0.0447 0.0102 1.0000
11.000 1.1971 0.03307 0.02649 -0.0435 0.0095 1.0000
11.250 1.2049 0.03456 0.02806 -0.0421 0.0089 1.0000
11.500 1.2110 0.03621 0.02980 -0.0407 0.0085 1.0000
11.750 1.2165 0.03794 0.03159 -0.0393 0.0080 1.0000
12.000 1.2200 0.03995 0.03369 -0.0378 0.0077 1.0000
12.250 1.2211 0.04227 0.03612 -0.0362 0.0074 1.0000
12.500 1.2229 0.04472 0.03869 -0.0344 0.0071 1.0000
12.750 1.2309 0.04661 0.04072 -0.0334 0.0069 1.0000
13.000 1.2391 0.04851 0.04275 -0.0324 0.0067 1.0000
13.250 1.2468 0.05057 0.04495 -0.0314 0.0066 1.0000
13.500 1.2538 0.05281 0.04735 -0.0305 0.0065 1.0000
13.750 1.2596 0.05524 0.04996 -0.0296 0.0064 1.0000
14.000 1.2631 0.05802 0.05292 -0.0288 0.0063 1.0000
14.250 1.2639 0.06127 0.05639 -0.0280 0.0063 1.0000
14.500 1.2616 0.06495 0.06032 -0.0274 0.0063 1.0000
14.750 1.2559 0.06906 0.06467 -0.0271 0.0064 1.0000
15.000 1.2466 0.07376 0.06961 -0.0271 0.0064 1.0000
15.250 1.2351 0.07888 0.07496 -0.0275 0.0064 1.0000
15.500 1.2199 0.08473 0.08104 -0.0285 0.0065 1.0000
15.750 1.2044 0.09081 0.08734 -0.0300 0.0066 1.0000
16.000 1.1864 0.09760 0.09434 -0.0322 0.0066 1.0000
16.250 1.1673 0.10493 0.10188 -0.0351 0.0067 1.0000
16.500 1.1473 0.11276 0.10990 -0.0387 0.0068 1.0000
16.750 1.1255 0.12147 0.11878 -0.0431 0.0069 1.0000
17.000 1.1026 0.13095 0.12844 -0.0484 0.0069 1.0000
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Polar data table (+)
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