NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 50,000 Max Cl/Cd: 29.02 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9615-il-50000.txt Download as CSV file: xf-npl9615-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4850 0.10803 0.10065 0.0101 1.0000 0.3677
-8.750 -0.4808 0.10507 0.09773 0.0109 1.0000 0.3870
-8.500 -0.4759 0.10212 0.09482 0.0119 1.0000 0.4072
-8.250 -0.4707 0.09917 0.09192 0.0131 1.0000 0.4277
-8.000 -0.4637 0.09610 0.08890 0.0142 1.0000 0.4488
-7.750 -0.4474 0.09247 0.08528 0.0154 1.0000 0.4723
-7.500 -0.4378 0.08921 0.08205 0.0165 1.0000 0.4940
-7.250 -0.4303 0.08605 0.07893 0.0176 1.0000 0.5149
-7.000 -0.4231 0.08225 0.07514 0.0173 1.0000 0.5189
-6.750 -0.6343 0.05693 0.04906 -0.0185 1.0000 0.1765
-6.500 -0.6293 0.05206 0.04373 -0.0169 1.0000 0.1580
-6.250 -0.6245 0.04825 0.03920 -0.0143 1.0000 0.1452
-6.000 -0.6111 0.04467 0.03538 -0.0124 1.0000 0.1409
-5.750 -0.5988 0.04163 0.03188 -0.0101 1.0000 0.1385
-5.500 -0.5837 0.03902 0.02891 -0.0079 1.0000 0.1398
-5.250 -0.5682 0.03697 0.02640 -0.0056 1.0000 0.1449
-5.000 -0.5494 0.03451 0.02370 -0.0040 1.0000 0.1498
-4.750 -0.5283 0.03250 0.02154 -0.0026 1.0000 0.1557
-4.500 -0.5079 0.03115 0.01972 -0.0008 1.0000 0.1624
-4.250 -0.4823 0.02901 0.01761 -0.0002 1.0000 0.1674
-4.000 -0.4568 0.02761 0.01613 0.0007 1.0000 0.1744
-3.750 -0.4295 0.02640 0.01475 0.0015 1.0000 0.1802
-3.500 -0.4013 0.02509 0.01358 0.0019 1.0000 0.1896
-3.250 -0.3748 0.02412 0.01258 0.0026 1.0000 0.1995
-3.000 -0.3518 0.02316 0.01168 0.0037 1.0000 0.2119
-2.750 -0.3321 0.02218 0.01085 0.0051 1.0000 0.2326
-2.500 -0.0245 0.02216 0.01273 -0.0288 1.0000 1.0000
-2.250 -0.0162 0.02167 0.01217 -0.0271 1.0000 1.0000
-2.000 -0.0102 0.02126 0.01170 -0.0250 1.0000 1.0000
-1.750 -0.0067 0.02091 0.01133 -0.0224 1.0000 1.0000
-1.500 -0.0060 0.02064 0.01104 -0.0192 1.0000 1.0000
-1.250 -0.0090 0.02046 0.01084 -0.0155 1.0000 1.0000
-1.000 -0.0154 0.02037 0.01073 -0.0112 1.0000 1.0000
-0.750 -0.0236 0.02038 0.01071 -0.0066 1.0000 1.0000
-0.500 -0.0312 0.02048 0.01076 -0.0021 1.0000 1.0000
-0.250 -0.0362 0.02067 0.01089 0.0019 1.0000 1.0000
0.000 -0.0377 0.02095 0.01109 0.0053 1.0000 1.0000
0.250 -0.0362 0.02132 0.01137 0.0080 1.0000 1.0000
0.500 -0.0322 0.02177 0.01173 0.0103 1.0000 1.0000
0.750 -0.0256 0.02230 0.01217 0.0121 1.0000 1.0000
1.000 -0.0106 0.02294 0.01276 0.0122 0.9978 1.0000
1.250 0.0527 0.02401 0.01379 0.0035 0.9784 1.0000
1.500 0.1157 0.02496 0.01472 -0.0047 0.9586 1.0000
1.750 0.1758 0.02572 0.01551 -0.0120 0.9379 1.0000
2.000 0.2285 0.02628 0.01614 -0.0175 0.9145 1.0000
2.250 0.2931 0.02662 0.01659 -0.0246 0.8917 1.0000
2.500 0.3635 0.02665 0.01678 -0.0320 0.8690 1.0000
2.750 0.4122 0.02661 0.01688 -0.0352 0.8430 1.0000
3.000 0.4682 0.02608 0.01650 -0.0385 0.8169 1.0000
3.250 0.5140 0.02550 0.01606 -0.0395 0.7898 1.0000
3.500 0.5499 0.02509 0.01573 -0.0389 0.7620 1.0000
3.750 0.5862 0.02457 0.01526 -0.0378 0.7340 1.0000
4.000 0.6080 0.02456 0.01529 -0.0350 0.7020 1.0000
4.250 0.6312 0.02445 0.01520 -0.0323 0.6688 1.0000
4.500 0.6538 0.02436 0.01507 -0.0293 0.6332 1.0000
4.750 0.6755 0.02436 0.01498 -0.0264 0.5956 1.0000
5.000 0.6969 0.02451 0.01499 -0.0236 0.5564 1.0000
5.250 0.7178 0.02487 0.01520 -0.0210 0.5173 1.0000
5.500 0.7380 0.02543 0.01558 -0.0185 0.4797 1.0000
5.750 0.7568 0.02620 0.01625 -0.0162 0.4449 1.0000
6.000 0.7748 0.02712 0.01713 -0.0141 0.4137 1.0000
6.250 0.7955 0.02800 0.01790 -0.0122 0.3871 1.0000
6.500 0.8132 0.02902 0.01895 -0.0102 0.3616 1.0000
6.750 0.8336 0.03000 0.01983 -0.0085 0.3388 1.0000
7.000 0.8529 0.03114 0.02091 -0.0067 0.3170 1.0000
7.250 0.8688 0.03241 0.02230 -0.0046 0.2948 1.0000
7.500 0.8866 0.03354 0.02336 -0.0027 0.2718 1.0000
7.750 0.9036 0.03486 0.02459 -0.0007 0.2488 1.0000
8.000 0.9175 0.03640 0.02619 0.0015 0.2260 1.0000
8.250 0.9338 0.03808 0.02776 0.0034 0.2044 1.0000
8.500 0.9448 0.04012 0.02997 0.0059 0.1858 1.0000
8.750 0.9598 0.04213 0.03198 0.0077 0.1698 1.0000
9.000 0.9720 0.04458 0.03457 0.0097 0.1579 1.0000
9.250 0.9771 0.04767 0.03804 0.0123 0.1499 1.0000
9.500 0.9868 0.05065 0.04120 0.0141 0.1432 1.0000
9.750 0.9859 0.05407 0.04500 0.0167 0.1385 1.0000
10.000 0.9894 0.05745 0.04856 0.0186 0.1344 1.0000
10.250 0.9734 0.06197 0.05352 0.0212 0.1336 1.0000
10.500 0.9530 0.06677 0.05862 0.0234 0.1336 1.0000
10.750 0.9284 0.07168 0.06375 0.0251 0.1343 1.0000
11.000 0.9028 0.07678 0.06896 0.0260 0.1351 1.0000
11.250 0.7446 0.10547 0.09759 0.0043 0.1642 1.0000
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Polar data table (+)
Polar graphs
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