NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 500,000 Max Cl/Cd: 64.58 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9627-il-500000-n5.txt Download as CSV file: xf-npl9627-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9077 0.13117 0.12818 0.0098 1.0000 0.0096
-16.750 -0.9519 0.11692 0.11375 0.0022 1.0000 0.0095
-16.500 -0.9848 0.10581 0.10248 -0.0039 1.0000 0.0094
-16.250 -1.0135 0.09607 0.09259 -0.0093 1.0000 0.0094
-16.000 -1.0399 0.08723 0.08360 -0.0142 1.0000 0.0093
-15.750 -1.0641 0.07903 0.07525 -0.0188 1.0000 0.0093
-15.500 -1.0853 0.07148 0.06755 -0.0232 1.0000 0.0093
-15.250 -1.1032 0.06450 0.06042 -0.0274 1.0000 0.0093
-15.000 -1.1178 0.05809 0.05384 -0.0314 1.0000 0.0093
-14.750 -1.1288 0.05238 0.04797 -0.0351 1.0000 0.0093
-14.500 -1.1369 0.04746 0.04288 -0.0381 1.0000 0.0093
-14.250 -1.1425 0.04331 0.03857 -0.0403 1.0000 0.0093
-14.000 -1.1462 0.03984 0.03494 -0.0415 1.0000 0.0094
-13.750 -1.1478 0.03698 0.03193 -0.0419 1.0000 0.0094
-13.500 -1.1475 0.03460 0.02941 -0.0415 1.0000 0.0094
-13.250 -1.1456 0.03259 0.02727 -0.0406 1.0000 0.0095
-13.000 -1.1421 0.03089 0.02544 -0.0392 1.0000 0.0095
-12.750 -1.1372 0.02943 0.02385 -0.0374 1.0000 0.0096
-12.500 -1.1309 0.02816 0.02246 -0.0353 1.0000 0.0097
-12.250 -1.1232 0.02704 0.02124 -0.0330 1.0000 0.0097
-12.000 -1.1117 0.02600 0.02009 -0.0312 1.0000 0.0098
-11.750 -1.0979 0.02503 0.01902 -0.0297 1.0000 0.0099
-11.500 -1.0856 0.02387 0.01778 -0.0280 1.0000 0.0100
-11.250 -1.0708 0.02287 0.01670 -0.0264 1.0000 0.0102
-11.000 -1.0543 0.02199 0.01575 -0.0250 1.0000 0.0103
-10.750 -1.0368 0.02118 0.01488 -0.0237 1.0000 0.0105
-10.500 -1.0184 0.02044 0.01406 -0.0225 1.0000 0.0108
-10.250 -0.9996 0.01974 0.01329 -0.0212 1.0000 0.0110
-10.000 -0.9804 0.01908 0.01256 -0.0199 1.0000 0.0113
-9.750 -0.9611 0.01845 0.01187 -0.0186 1.0000 0.0116
-9.500 -0.9416 0.01787 0.01121 -0.0173 1.0000 0.0120
-9.250 -0.9224 0.01729 0.01059 -0.0159 1.0000 0.0124
-9.000 -0.9029 0.01677 0.01005 -0.0145 1.0000 0.0128
-8.750 -0.8829 0.01631 0.00956 -0.0131 1.0000 0.0133
-8.500 -0.8628 0.01589 0.00911 -0.0117 1.0000 0.0139
-8.250 -0.8427 0.01549 0.00867 -0.0104 1.0000 0.0144
-8.000 -0.8224 0.01512 0.00830 -0.0090 1.0000 0.0150
-7.750 -0.7932 0.01475 0.00791 -0.0095 0.9981 0.0159
-7.500 -0.7599 0.01436 0.00749 -0.0108 0.9952 0.0170
-7.250 -0.7267 0.01400 0.00712 -0.0122 0.9928 0.0182
-7.000 -0.6957 0.01366 0.00675 -0.0130 0.9892 0.0195
-6.750 -0.6638 0.01333 0.00639 -0.0139 0.9856 0.0208
-6.500 -0.6307 0.01301 0.00606 -0.0152 0.9824 0.0223
-6.250 -0.5987 0.01271 0.00574 -0.0161 0.9783 0.0239
-6.000 -0.5687 0.01240 0.00543 -0.0167 0.9724 0.0255
-5.750 -0.5361 0.01212 0.00512 -0.0177 0.9675 0.0269
-5.500 -0.5064 0.01183 0.00482 -0.0181 0.9594 0.0282
-5.250 -0.4744 0.01155 0.00453 -0.0190 0.9514 0.0299
-4.750 -0.4170 0.01106 0.00402 -0.0191 0.9290 0.0331
-4.500 -0.3888 0.01085 0.00377 -0.0191 0.9171 0.0355
-4.250 -0.3617 0.01062 0.00354 -0.0188 0.9027 0.0396
-4.000 -0.3353 0.01036 0.00329 -0.0184 0.8874 0.0479
-3.750 -0.3103 0.00992 0.00299 -0.0178 0.8717 0.0830
-3.500 -0.2857 0.00945 0.00273 -0.0172 0.8547 0.1386
-3.250 -0.2606 0.00910 0.00252 -0.0166 0.8364 0.1851
-3.000 -0.2349 0.00884 0.00235 -0.0161 0.8176 0.2249
-2.500 -0.1827 0.00847 0.00210 -0.0153 0.7790 0.2931
-2.250 -0.1567 0.00834 0.00200 -0.0148 0.7555 0.3255
-2.000 -0.1304 0.00824 0.00193 -0.0144 0.7319 0.3596
-1.750 -0.1039 0.00815 0.00186 -0.0141 0.7110 0.3891
-1.500 -0.0771 0.00808 0.00179 -0.0137 0.6920 0.4150
-1.250 -0.0505 0.00799 0.00173 -0.0134 0.6724 0.4417
-0.750 0.0023 0.00783 0.00163 -0.0127 0.6302 0.5055
-0.500 0.0285 0.00771 0.00160 -0.0123 0.6129 0.5448
-0.250 0.0545 0.00759 0.00159 -0.0118 0.5955 0.5927
0.000 0.0802 0.00749 0.00159 -0.0113 0.5754 0.6409
0.250 0.1061 0.00743 0.00160 -0.0108 0.5554 0.6854
0.500 0.1322 0.00738 0.00163 -0.0102 0.5386 0.7251
0.750 0.1584 0.00735 0.00167 -0.0097 0.5246 0.7614
1.000 0.1847 0.00736 0.00172 -0.0092 0.5078 0.7942
1.250 0.2109 0.00739 0.00179 -0.0086 0.4875 0.8223
1.500 0.2374 0.00746 0.00185 -0.0081 0.4658 0.8475
1.750 0.2637 0.00758 0.00193 -0.0076 0.4415 0.8687
2.000 0.2904 0.00771 0.00202 -0.0071 0.4191 0.8878
2.250 0.3174 0.00788 0.00211 -0.0068 0.3933 0.9042
2.500 0.3446 0.00807 0.00222 -0.0065 0.3659 0.9190
2.750 0.3728 0.00829 0.00234 -0.0065 0.3386 0.9315
3.000 0.4017 0.00856 0.00248 -0.0067 0.3064 0.9420
3.250 0.4301 0.00884 0.00263 -0.0069 0.2762 0.9522
3.500 0.4614 0.00913 0.00281 -0.0076 0.2497 0.9601
3.750 0.4919 0.00942 0.00298 -0.0083 0.2240 0.9683
4.000 0.5243 0.00977 0.00319 -0.0094 0.1913 0.9749
4.250 0.5551 0.01023 0.00344 -0.0102 0.1517 0.9814
4.500 0.5893 0.01072 0.00374 -0.0119 0.1137 0.9851
4.750 0.6223 0.01111 0.00401 -0.0132 0.0942 0.9891
5.000 0.6546 0.01142 0.00427 -0.0144 0.0857 0.9929
5.250 0.6884 0.01174 0.00453 -0.0158 0.0799 0.9952
5.500 0.7223 0.01199 0.00478 -0.0172 0.0768 0.9979
5.750 0.7537 0.01227 0.00505 -0.0182 0.0737 1.0000
6.000 0.7751 0.01256 0.00532 -0.0170 0.0713 1.0000
6.250 0.7969 0.01280 0.00558 -0.0159 0.0698 1.0000
6.500 0.8190 0.01304 0.00583 -0.0148 0.0685 1.0000
6.750 0.8410 0.01329 0.00611 -0.0137 0.0670 1.0000
7.000 0.8629 0.01357 0.00640 -0.0126 0.0654 1.0000
7.250 0.8845 0.01390 0.00672 -0.0115 0.0637 1.0000
7.500 0.9055 0.01428 0.00711 -0.0103 0.0620 1.0000
7.750 0.9281 0.01453 0.00740 -0.0094 0.0608 1.0000
8.000 0.9507 0.01481 0.00771 -0.0085 0.0592 1.0000
8.250 0.9733 0.01512 0.00804 -0.0076 0.0575 1.0000
8.500 0.9954 0.01547 0.00840 -0.0067 0.0558 1.0000
8.750 1.0176 0.01585 0.00879 -0.0058 0.0541 1.0000
9.000 1.0408 0.01614 0.00914 -0.0051 0.0523 1.0000
9.250 1.0637 0.01647 0.00949 -0.0044 0.0502 1.0000
9.500 1.0860 0.01685 0.00987 -0.0036 0.0483 1.0000
9.750 1.1086 0.01720 0.01028 -0.0029 0.0462 1.0000
10.000 1.1310 0.01757 0.01067 -0.0021 0.0441 1.0000
10.250 1.1526 0.01799 0.01109 -0.0013 0.0422 1.0000
10.500 1.1741 0.01841 0.01157 -0.0004 0.0403 1.0000
10.750 1.1951 0.01886 0.01203 0.0004 0.0383 1.0000
11.000 1.2151 0.01938 0.01257 0.0014 0.0369 1.0000
11.250 1.2345 0.01991 0.01316 0.0025 0.0357 1.0000
11.500 1.2532 0.02048 0.01377 0.0036 0.0346 1.0000
11.750 1.2708 0.02109 0.01441 0.0049 0.0337 1.0000
12.000 1.2863 0.02178 0.01513 0.0064 0.0328 1.0000
12.250 1.3003 0.02243 0.01587 0.0082 0.0322 1.0000
12.500 1.3136 0.02315 0.01665 0.0099 0.0315 1.0000
12.750 1.3264 0.02393 0.01750 0.0116 0.0307 1.0000
13.000 1.3382 0.02481 0.01844 0.0132 0.0299 1.0000
13.250 1.3485 0.02583 0.01951 0.0147 0.0292 1.0000
13.500 1.3575 0.02700 0.02074 0.0162 0.0286 1.0000
13.750 1.3679 0.02813 0.02197 0.0174 0.0280 1.0000
14.000 1.3773 0.02940 0.02334 0.0184 0.0274 1.0000
14.250 1.3857 0.03083 0.02486 0.0193 0.0268 1.0000
14.500 1.3927 0.03246 0.02658 0.0199 0.0263 1.0000
14.750 1.3982 0.03433 0.02853 0.0204 0.0259 1.0000
15.000 1.4020 0.03649 0.03077 0.0205 0.0254 1.0000
15.250 1.4034 0.03902 0.03339 0.0204 0.0250 1.0000
15.500 1.4056 0.04159 0.03607 0.0201 0.0247 1.0000
15.750 1.4076 0.04426 0.03887 0.0196 0.0244 1.0000
16.000 1.4082 0.04721 0.04193 0.0189 0.0241 1.0000
16.250 1.4068 0.05048 0.04533 0.0180 0.0237 1.0000
16.500 1.4037 0.05403 0.04900 0.0168 0.0234 1.0000
16.750 1.3988 0.05792 0.05301 0.0155 0.0231 1.0000
17.000 1.3920 0.06211 0.05732 0.0139 0.0229 1.0000
17.250 1.3833 0.06669 0.06201 0.0121 0.0226 1.0000
17.500 1.3728 0.07168 0.06712 0.0099 0.0224 1.0000
17.750 1.3607 0.07701 0.07256 0.0076 0.0222 1.0000
18.000 1.3467 0.08278 0.07845 0.0050 0.0220 1.0000
18.250 1.3315 0.08888 0.08467 0.0021 0.0219 1.0000
18.500 1.3148 0.09531 0.09121 -0.0010 0.0217 1.0000
18.750 1.2977 0.10196 0.09797 -0.0042 0.0216 1.0000
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