NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 200,000 Max Cl/Cd: 54.27 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9627-il-200000.txt Download as CSV file: xf-npl9627-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9627 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4870 0.10002 0.09646 -0.0172 1.0000 0.0797
-10.500 -0.7630 0.04768 0.04317 -0.0451 1.0000 0.0395
-10.250 -0.8780 0.04907 0.04347 -0.0351 1.0000 0.0354
-10.000 -0.8690 0.04571 0.04002 -0.0339 1.0000 0.0350
-9.750 -0.8651 0.04235 0.03639 -0.0320 1.0000 0.0344
-9.500 -0.8609 0.03902 0.03270 -0.0297 1.0000 0.0339
-9.250 -0.8533 0.03603 0.02933 -0.0274 1.0000 0.0337
-9.000 -0.8420 0.03347 0.02642 -0.0252 1.0000 0.0339
-8.750 -0.8286 0.03124 0.02383 -0.0232 1.0000 0.0344
-8.500 -0.8141 0.02932 0.02150 -0.0210 1.0000 0.0353
-8.250 -0.7963 0.02738 0.01937 -0.0194 1.0000 0.0363
-8.000 -0.7759 0.02605 0.01808 -0.0183 1.0000 0.0377
-7.750 -0.7566 0.02483 0.01670 -0.0168 1.0000 0.0393
-7.500 -0.7372 0.02367 0.01531 -0.0152 1.0000 0.0408
-7.250 -0.7171 0.02249 0.01423 -0.0140 1.0000 0.0428
-7.000 -0.6978 0.02191 0.01350 -0.0125 1.0000 0.0458
-6.750 -0.6786 0.02078 0.01251 -0.0112 1.0000 0.0487
-6.500 -0.6589 0.02004 0.01169 -0.0096 1.0000 0.0515
-6.250 -0.6409 0.01894 0.01069 -0.0079 1.0000 0.0542
-6.000 -0.6223 0.01820 0.00995 -0.0062 1.0000 0.0573
-5.750 -0.6048 0.01734 0.00912 -0.0044 1.0000 0.0604
-5.500 -0.5867 0.01668 0.00849 -0.0028 1.0000 0.0642
-5.250 -0.5684 0.01603 0.00784 -0.0011 1.0000 0.0684
-5.000 -0.5491 0.01552 0.00734 0.0003 1.0000 0.0741
-4.750 -0.5297 0.01497 0.00684 0.0016 1.0000 0.0827
-4.500 -0.5102 0.01430 0.00636 0.0029 1.0000 0.1043
-4.250 -0.4921 0.01303 0.00592 0.0038 1.0000 0.2386
-4.000 -0.4713 0.01266 0.00584 0.0047 1.0000 0.3104
-3.750 -0.4369 0.01245 0.00579 0.0029 0.9964 0.3605
-3.500 -0.3932 0.01226 0.00569 -0.0006 0.9901 0.4021
-3.250 -0.3511 0.01198 0.00557 -0.0037 0.9830 0.4446
-3.000 -0.3105 0.01170 0.00544 -0.0064 0.9756 0.4861
-2.750 -0.2690 0.01135 0.00530 -0.0093 0.9686 0.5308
-2.500 -0.2313 0.01097 0.00519 -0.0112 0.9601 0.5865
-2.250 -0.1906 0.01058 0.00511 -0.0135 0.9535 0.6539
-2.000 -0.1563 0.01027 0.00506 -0.0142 0.9433 0.7172
-1.750 -0.1184 0.01003 0.00501 -0.0154 0.9357 0.7743
-1.500 -0.0878 0.00992 0.00501 -0.0149 0.9223 0.8185
-1.250 -0.0566 0.00987 0.00500 -0.0144 0.9081 0.8539
-1.000 -0.0266 0.00986 0.00498 -0.0137 0.8927 0.8835
-0.750 0.0063 0.00992 0.00500 -0.0136 0.8767 0.9047
-0.500 0.0398 0.01000 0.00502 -0.0136 0.8593 0.9228
-0.250 0.0748 0.01011 0.00504 -0.0142 0.8401 0.9380
0.000 0.1113 0.01022 0.00504 -0.0151 0.8194 0.9515
0.250 0.1579 0.01032 0.00502 -0.0183 0.7980 0.9593
0.750 0.2410 0.01051 0.00498 -0.0232 0.7539 0.9791
1.000 0.2859 0.01055 0.00489 -0.0266 0.7294 0.9867
1.250 0.3288 0.01061 0.00479 -0.0295 0.7053 0.9946
1.500 0.3686 0.01062 0.00470 -0.0321 0.6792 1.0000
1.750 0.3921 0.01065 0.00461 -0.0313 0.6564 1.0000
2.000 0.4158 0.01070 0.00454 -0.0306 0.6348 1.0000
2.250 0.4396 0.01075 0.00450 -0.0299 0.6126 1.0000
2.500 0.4635 0.01082 0.00449 -0.0292 0.5909 1.0000
2.750 0.4871 0.01091 0.00450 -0.0284 0.5694 1.0000
3.000 0.5102 0.01102 0.00451 -0.0275 0.5463 1.0000
3.250 0.5331 0.01114 0.00454 -0.0266 0.5221 1.0000
3.500 0.5560 0.01127 0.00461 -0.0257 0.4987 1.0000
3.750 0.5787 0.01143 0.00469 -0.0247 0.4757 1.0000
4.000 0.6012 0.01159 0.00479 -0.0237 0.4514 1.0000
4.250 0.6234 0.01179 0.00491 -0.0226 0.4255 1.0000
4.500 0.6452 0.01203 0.00506 -0.0215 0.3979 1.0000
4.750 0.6665 0.01231 0.00523 -0.0203 0.3661 1.0000
5.000 0.6870 0.01266 0.00544 -0.0189 0.3282 1.0000
5.250 0.7061 0.01316 0.00571 -0.0175 0.2806 1.0000
5.500 0.7226 0.01395 0.00614 -0.0157 0.2129 1.0000
5.750 0.7387 0.01487 0.00671 -0.0138 0.1638 1.0000
6.000 0.7568 0.01558 0.00727 -0.0122 0.1460 1.0000
6.250 0.7758 0.01620 0.00782 -0.0107 0.1357 1.0000
6.500 0.7943 0.01687 0.00839 -0.0091 0.1277 1.0000
6.750 0.8149 0.01737 0.00892 -0.0078 0.1214 1.0000
7.000 0.8345 0.01799 0.00949 -0.0065 0.1160 1.0000
7.250 0.8541 0.01870 0.01018 -0.0052 0.1117 1.0000
7.500 0.8751 0.01926 0.01079 -0.0040 0.1074 1.0000
7.750 0.8952 0.02000 0.01148 -0.0029 0.1035 1.0000
8.000 0.9156 0.02090 0.01237 -0.0017 0.1000 1.0000
8.250 0.9370 0.02156 0.01311 -0.0007 0.0963 1.0000
8.500 0.9578 0.02236 0.01388 0.0002 0.0925 1.0000
8.750 0.9789 0.02352 0.01502 0.0011 0.0890 1.0000
9.000 0.9999 0.02430 0.01592 0.0021 0.0854 1.0000
9.250 1.0213 0.02525 0.01686 0.0029 0.0823 1.0000
9.500 1.0442 0.02690 0.01847 0.0033 0.0795 1.0000
9.750 1.0639 0.02784 0.01961 0.0044 0.0770 1.0000
10.000 1.0841 0.02888 0.02076 0.0054 0.0744 1.0000
10.250 1.1055 0.03005 0.02192 0.0060 0.0722 1.0000
10.500 1.1277 0.03218 0.02408 0.0062 0.0702 1.0000
10.750 1.1427 0.03333 0.02553 0.0079 0.0686 1.0000
11.000 1.1585 0.03467 0.02708 0.0092 0.0667 1.0000
11.250 1.1760 0.03594 0.02845 0.0102 0.0650 1.0000
11.500 1.1937 0.03733 0.02987 0.0111 0.0634 1.0000
11.750 1.2115 0.03996 0.03254 0.0115 0.0619 1.0000
12.000 1.2143 0.04150 0.03448 0.0142 0.0609 1.0000
12.250 1.2163 0.04350 0.03681 0.0167 0.0598 1.0000
12.500 1.2174 0.04556 0.03913 0.0190 0.0587 1.0000
12.750 1.2170 0.04744 0.04120 0.0215 0.0577 1.0000
13.000 1.2221 0.04902 0.04286 0.0233 0.0567 1.0000
13.250 1.2378 0.05034 0.04414 0.0239 0.0555 1.0000
13.500 1.2421 0.05339 0.04724 0.0249 0.0546 1.0000
13.750 1.2198 0.05624 0.05040 0.0276 0.0543 1.0000
14.000 1.1957 0.05994 0.05440 0.0289 0.0540 1.0000
14.250 1.1695 0.06453 0.05927 0.0287 0.0539 1.0000
14.500 1.1411 0.07013 0.06514 0.0271 0.0538 1.0000
14.750 1.1099 0.07690 0.07214 0.0239 0.0539 1.0000
15.000 1.0758 0.08495 0.08041 0.0194 0.0541 1.0000
15.250 1.0397 0.09430 0.08993 0.0138 0.0543 1.0000
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