NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 500,000 Max Cl/Cd: 70.82 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9615-il-500000.txt Download as CSV file: xf-npl9615-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5868 0.08986 0.08739 -0.0203 1.0000 0.0306
-10.000 -0.6006 0.08124 0.07881 -0.0273 1.0000 0.0310
-9.750 -0.8238 0.04230 0.03857 -0.0316 1.0000 0.0208
-9.500 -0.8267 0.03939 0.03548 -0.0284 1.0000 0.0206
-9.250 -0.8327 0.03552 0.03131 -0.0246 1.0000 0.0204
-9.000 -0.8400 0.03088 0.02621 -0.0201 1.0000 0.0202
-8.750 -0.8441 0.02606 0.02082 -0.0156 1.0000 0.0197
-8.500 -0.8379 0.02266 0.01695 -0.0122 1.0000 0.0193
-8.250 -0.8243 0.02086 0.01491 -0.0098 1.0000 0.0192
-8.000 -0.8091 0.01957 0.01343 -0.0076 1.0000 0.0192
-7.750 -0.7932 0.01853 0.01226 -0.0054 1.0000 0.0192
-7.500 -0.7770 0.01765 0.01129 -0.0033 1.0000 0.0192
-7.250 -0.7606 0.01689 0.01044 -0.0012 1.0000 0.0193
-7.000 -0.7438 0.01622 0.00970 0.0008 1.0000 0.0194
-6.750 -0.7265 0.01561 0.00903 0.0027 1.0000 0.0195
-6.500 -0.7042 0.01501 0.00837 0.0036 0.9995 0.0197
-6.250 -0.6691 0.01437 0.00767 0.0019 0.9969 0.0200
-6.000 -0.6339 0.01380 0.00705 0.0001 0.9938 0.0204
-5.750 -0.5980 0.01329 0.00649 -0.0017 0.9910 0.0209
-5.500 -0.5631 0.01280 0.00601 -0.0034 0.9882 0.0218
-5.250 -0.5313 0.01242 0.00564 -0.0043 0.9837 0.0232
-5.000 -0.4967 0.01208 0.00531 -0.0058 0.9796 0.0255
-4.750 -0.4602 0.01179 0.00503 -0.0077 0.9762 0.0290
-4.500 -0.4225 0.01155 0.00476 -0.0098 0.9736 0.0327
-4.250 -0.3911 0.01132 0.00454 -0.0106 0.9683 0.0355
-4.000 -0.3570 0.01105 0.00426 -0.0119 0.9640 0.0377
-3.750 -0.3200 0.01080 0.00403 -0.0139 0.9605 0.0400
-3.500 -0.2820 0.01053 0.00377 -0.0161 0.9572 0.0422
-3.250 -0.2512 0.01032 0.00356 -0.0166 0.9490 0.0443
-3.000 -0.2152 0.01008 0.00333 -0.0183 0.9418 0.0473
-2.750 -0.1847 0.00987 0.00312 -0.0187 0.9301 0.0499
-2.500 -0.1533 0.00967 0.00291 -0.0194 0.9188 0.0528
-2.250 -0.1236 0.00949 0.00272 -0.0196 0.9061 0.0568
-2.000 -0.0962 0.00931 0.00255 -0.0194 0.8924 0.0622
-1.750 -0.0689 0.00914 0.00238 -0.0191 0.8783 0.0707
-1.500 -0.0436 0.00886 0.00221 -0.0185 0.8618 0.1024
-1.250 -0.0344 0.00725 0.00185 -0.0153 0.8389 0.4570
-1.000 -0.0163 0.00674 0.00173 -0.0132 0.8097 0.5778
-0.750 0.0028 0.00646 0.00166 -0.0110 0.7867 0.6676
-0.500 0.0232 0.00630 0.00166 -0.0091 0.7677 0.7397
0.000 0.0704 0.00617 0.00180 -0.0064 0.7323 0.8379
0.250 0.0946 0.00622 0.00183 -0.0053 0.7114 0.8684
0.500 0.1226 0.00631 0.00191 -0.0049 0.6860 0.8960
0.750 0.1517 0.00650 0.00203 -0.0046 0.6612 0.9225
1.000 0.1849 0.00669 0.00215 -0.0054 0.6366 0.9371
1.250 0.2143 0.00689 0.00223 -0.0054 0.6120 0.9494
1.500 0.2532 0.00711 0.00234 -0.0077 0.5886 0.9541
1.750 0.2899 0.00729 0.00243 -0.0095 0.5675 0.9581
2.000 0.3237 0.00746 0.00251 -0.0107 0.5477 0.9631
2.250 0.3547 0.00762 0.00260 -0.0113 0.5284 0.9688
2.500 0.3934 0.00778 0.00268 -0.0137 0.5071 0.9714
2.750 0.4308 0.00794 0.00276 -0.0158 0.4856 0.9747
3.000 0.4663 0.00812 0.00285 -0.0175 0.4637 0.9788
3.250 0.4996 0.00830 0.00296 -0.0187 0.4408 0.9835
3.500 0.5311 0.00851 0.00307 -0.0196 0.4143 0.9877
3.750 0.5686 0.00871 0.00315 -0.0219 0.3818 0.9903
4.000 0.6044 0.00898 0.00326 -0.0238 0.3426 0.9934
4.250 0.6389 0.00932 0.00340 -0.0256 0.2974 0.9965
5.000 0.7215 0.01039 0.00398 -0.0264 0.1951 1.0000
5.250 0.7427 0.01070 0.00418 -0.0254 0.1740 1.0000
5.500 0.7637 0.01097 0.00439 -0.0242 0.1592 1.0000
5.750 0.7846 0.01123 0.00460 -0.0230 0.1483 1.0000
6.000 0.8053 0.01148 0.00483 -0.0217 0.1390 1.0000
6.250 0.8258 0.01173 0.00506 -0.0204 0.1306 1.0000
6.500 0.8463 0.01198 0.00530 -0.0190 0.1227 1.0000
6.750 0.8666 0.01224 0.00555 -0.0177 0.1148 1.0000
7.000 0.8867 0.01252 0.00581 -0.0163 0.1066 1.0000
7.250 0.9065 0.01284 0.00610 -0.0149 0.0969 1.0000
7.500 0.9265 0.01317 0.00636 -0.0135 0.0833 1.0000
7.750 0.9450 0.01361 0.00675 -0.0118 0.0659 1.0000
8.000 0.9614 0.01427 0.00729 -0.0098 0.0496 1.0000
8.250 0.9782 0.01489 0.00785 -0.0079 0.0411 1.0000
8.500 0.9957 0.01546 0.00842 -0.0062 0.0367 1.0000
8.750 1.0129 0.01606 0.00902 -0.0043 0.0339 1.0000
9.000 1.0304 0.01662 0.00961 -0.0026 0.0317 1.0000
9.250 1.0470 0.01724 0.01026 -0.0007 0.0299 1.0000
9.500 1.0631 0.01788 0.01093 0.0012 0.0283 1.0000
9.750 1.0786 0.01855 0.01165 0.0031 0.0269 1.0000
10.000 1.0940 0.01921 0.01234 0.0051 0.0256 1.0000
10.250 1.1063 0.02008 0.01323 0.0074 0.0246 1.0000
10.500 1.1210 0.02078 0.01402 0.0094 0.0237 1.0000
10.750 1.1342 0.02157 0.01485 0.0115 0.0230 1.0000
11.000 1.1448 0.02249 0.01579 0.0138 0.0224 1.0000
11.250 1.1510 0.02357 0.01690 0.0168 0.0219 1.0000
11.500 1.1610 0.02444 0.01786 0.0193 0.0215 1.0000
11.750 1.1701 0.02542 0.01894 0.0216 0.0211 1.0000
12.000 1.1787 0.02650 0.02010 0.0237 0.0207 1.0000
12.250 1.1869 0.02767 0.02134 0.0256 0.0204 1.0000
12.500 1.1946 0.02894 0.02267 0.0274 0.0201 1.0000
12.750 1.2017 0.03035 0.02412 0.0290 0.0198 1.0000
13.000 1.2080 0.03192 0.02574 0.0304 0.0196 1.0000
13.250 1.2137 0.03377 0.02761 0.0318 0.0194 1.0000
13.500 1.2194 0.03551 0.02947 0.0330 0.0192 1.0000
13.750 1.2241 0.03738 0.03148 0.0339 0.0191 1.0000
14.000 1.2277 0.03944 0.03368 0.0346 0.0190 1.0000
14.250 1.2303 0.04170 0.03608 0.0351 0.0188 1.0000
14.500 1.2315 0.04417 0.03869 0.0354 0.0187 1.0000
14.750 1.2315 0.04687 0.04154 0.0355 0.0186 1.0000
15.000 1.2299 0.04982 0.04464 0.0352 0.0184 1.0000
15.250 1.2269 0.05304 0.04801 0.0346 0.0183 1.0000
15.500 1.2226 0.05652 0.05163 0.0337 0.0182 1.0000
15.750 1.2170 0.06031 0.05556 0.0325 0.0181 1.0000
16.000 1.2099 0.06439 0.05979 0.0310 0.0180 1.0000
16.250 1.2010 0.06889 0.06443 0.0292 0.0179 1.0000
16.500 1.1901 0.07387 0.06957 0.0269 0.0179 1.0000
16.750 1.1765 0.07949 0.07536 0.0242 0.0179 1.0000
17.000 1.1601 0.08585 0.08190 0.0208 0.0179 1.0000
17.250 1.1409 0.09298 0.08922 0.0168 0.0179 1.0000
17.500 1.1183 0.10114 0.09756 0.0120 0.0180 1.0000
17.750 1.0919 0.11045 0.10708 0.0064 0.0181 1.0000
18.000 1.0597 0.12160 0.11845 -0.0005 0.0183 1.0000
18.250 1.0193 0.13537 0.13244 -0.0092 0.0186 1.0000
18.500 0.9581 0.15576 0.15307 -0.0219 0.0191 1.0000
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