NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 500,000 Max Cl/Cd: 69.74 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9660-il-500000.txt Download as CSV file: xf-npl9660-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9660 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 -0.6365 0.09242 0.09015 -0.0059 1.0000 0.0301
-10.000 -0.6435 0.08520 0.08295 -0.0117 1.0000 0.0303
-9.750 -0.8239 0.04627 0.04290 -0.0275 1.0000 0.0213
-9.500 -0.8216 0.04290 0.03933 -0.0265 1.0000 0.0211
-9.250 -0.8202 0.03868 0.03482 -0.0251 1.0000 0.0208
-9.000 -0.8415 0.02786 0.02293 -0.0210 1.0000 0.0199
-8.750 -0.8358 0.02264 0.01700 -0.0184 1.0000 0.0194
-8.500 -0.8193 0.02087 0.01498 -0.0167 1.0000 0.0194
-8.250 -0.8026 0.01963 0.01358 -0.0150 1.0000 0.0194
-8.000 -0.7857 0.01863 0.01246 -0.0132 1.0000 0.0194
-7.750 -0.7686 0.01777 0.01151 -0.0114 1.0000 0.0196
-7.500 -0.7510 0.01702 0.01067 -0.0096 1.0000 0.0197
-7.250 -0.7330 0.01633 0.00992 -0.0080 1.0000 0.0199
-7.000 -0.7145 0.01571 0.00924 -0.0064 1.0000 0.0201
-6.750 -0.6873 0.01505 0.00851 -0.0066 0.9988 0.0204
-6.500 -0.6533 0.01438 0.00778 -0.0082 0.9964 0.0209
-6.250 -0.6181 0.01378 0.00712 -0.0100 0.9941 0.0215
-6.000 -0.5832 0.01325 0.00662 -0.0117 0.9916 0.0225
-5.750 -0.5475 0.01287 0.00623 -0.0136 0.9891 0.0241
-5.500 -0.5100 0.01254 0.00591 -0.0157 0.9870 0.0266
-5.250 -0.4710 0.01226 0.00562 -0.0182 0.9853 0.0302
-5.000 -0.4325 0.01206 0.00541 -0.0205 0.9833 0.0334
-4.750 -0.3986 0.01181 0.00518 -0.0219 0.9795 0.0360
-4.500 -0.3656 0.01166 0.00501 -0.0230 0.9751 0.0385
-4.250 -0.3340 0.01144 0.00478 -0.0238 0.9709 0.0403
-4.000 -0.3095 0.01131 0.00466 -0.0230 0.9636 0.0419
-3.750 -0.2850 0.01121 0.00455 -0.0222 0.9567 0.0434
-3.500 -0.2618 0.01110 0.00442 -0.0210 0.9492 0.0449
-3.250 -0.2380 0.01087 0.00419 -0.0200 0.9407 0.0464
-3.000 -0.2150 0.01064 0.00397 -0.0187 0.9331 0.0483
-2.750 -0.1915 0.01040 0.00374 -0.0176 0.9245 0.0502
-2.500 -0.1677 0.01020 0.00352 -0.0164 0.9170 0.0524
-2.250 -0.1436 0.00993 0.00327 -0.0154 0.9078 0.0560
-2.000 -0.1186 0.00971 0.00306 -0.0145 0.8982 0.0607
-1.750 -0.0938 0.00946 0.00283 -0.0136 0.8879 0.0680
-1.500 -0.0675 0.00919 0.00263 -0.0131 0.8750 0.0844
-1.250 -0.0476 0.00734 0.00217 -0.0126 0.8612 0.4620
-1.000 -0.0241 0.00663 0.00202 -0.0118 0.8454 0.6144
-0.750 0.0007 0.00630 0.00194 -0.0109 0.8282 0.6962
-0.500 0.0256 0.00609 0.00191 -0.0098 0.8076 0.7552
-0.250 0.0507 0.00603 0.00191 -0.0088 0.7839 0.8003
0.000 0.0751 0.00607 0.00195 -0.0076 0.7598 0.8361
0.250 0.0997 0.00618 0.00203 -0.0064 0.7348 0.8614
0.500 0.1243 0.00636 0.00211 -0.0053 0.7101 0.8833
0.750 0.1481 0.00657 0.00222 -0.0039 0.6851 0.8994
1.000 0.1709 0.00678 0.00236 -0.0024 0.6591 0.9124
1.250 0.1908 0.00705 0.00255 0.0000 0.6358 0.9271
1.500 0.2103 0.00728 0.00270 0.0024 0.6144 0.9414
1.750 0.2332 0.00739 0.00273 0.0038 0.5951 0.9513
2.000 0.2575 0.00748 0.00273 0.0048 0.5761 0.9595
2.250 0.2842 0.00748 0.00267 0.0052 0.5575 0.9653
2.500 0.3113 0.00752 0.00264 0.0054 0.5390 0.9717
2.750 0.3450 0.00760 0.00264 0.0042 0.5190 0.9755
3.250 0.4126 0.00783 0.00272 0.0016 0.4781 0.9832
3.500 0.4509 0.00798 0.00280 -0.0008 0.4552 0.9849
3.750 0.4891 0.00818 0.00291 -0.0031 0.4286 0.9866
4.000 0.5262 0.00839 0.00301 -0.0053 0.3985 0.9887
4.250 0.5617 0.00865 0.00313 -0.0072 0.3616 0.9912
4.500 0.5962 0.00899 0.00329 -0.0089 0.3187 0.9937
4.750 0.6316 0.00939 0.00349 -0.0109 0.2720 0.9958
5.000 0.6661 0.00981 0.00373 -0.0127 0.2361 0.9982
5.250 0.6985 0.01022 0.00398 -0.0141 0.2040 1.0000
5.500 0.7209 0.01056 0.00420 -0.0134 0.1818 1.0000
5.750 0.7433 0.01084 0.00442 -0.0126 0.1670 1.0000
6.000 0.7655 0.01110 0.00465 -0.0117 0.1556 1.0000
6.250 0.7875 0.01136 0.00489 -0.0108 0.1455 1.0000
6.500 0.8090 0.01165 0.00513 -0.0098 0.1357 1.0000
6.750 0.8303 0.01194 0.00539 -0.0088 0.1260 1.0000
7.000 0.8518 0.01222 0.00565 -0.0078 0.1161 1.0000
7.250 0.8732 0.01252 0.00593 -0.0068 0.1060 1.0000
7.500 0.8950 0.01288 0.00624 -0.0059 0.0949 1.0000
7.750 0.9179 0.01325 0.00655 -0.0053 0.0754 1.0000
8.000 0.9391 0.01395 0.00711 -0.0045 0.0556 1.0000
8.250 0.9610 0.01465 0.00772 -0.0039 0.0426 1.0000
8.500 0.9838 0.01528 0.00833 -0.0034 0.0371 1.0000
8.750 1.0064 0.01594 0.00899 -0.0029 0.0338 1.0000
9.000 1.0295 0.01653 0.00963 -0.0024 0.0315 1.0000
9.250 1.0509 0.01733 0.01045 -0.0018 0.0297 1.0000
9.500 1.0737 0.01793 0.01112 -0.0014 0.0281 1.0000
9.750 1.0951 0.01865 0.01188 -0.0008 0.0267 1.0000
10.000 1.1125 0.01976 0.01301 0.0002 0.0255 1.0000
10.250 1.1334 0.02047 0.01381 0.0009 0.0246 1.0000
10.500 1.1527 0.02129 0.01471 0.0017 0.0237 1.0000
10.750 1.1707 0.02218 0.01565 0.0026 0.0229 1.0000
11.000 1.1860 0.02326 0.01676 0.0038 0.0223 1.0000
11.250 1.1946 0.02488 0.01843 0.0057 0.0217 1.0000
11.500 1.2077 0.02586 0.01951 0.0072 0.0214 1.0000
11.750 1.2199 0.02696 0.02072 0.0087 0.0210 1.0000
12.000 1.2307 0.02820 0.02206 0.0101 0.0207 1.0000
12.250 1.2407 0.02954 0.02350 0.0115 0.0204 1.0000
12.500 1.2496 0.03101 0.02507 0.0128 0.0201 1.0000
12.750 1.2578 0.03259 0.02675 0.0140 0.0198 1.0000
13.000 1.2650 0.03430 0.02856 0.0151 0.0196 1.0000
13.250 1.2712 0.03614 0.03051 0.0160 0.0194 1.0000
13.500 1.2768 0.03809 0.03255 0.0166 0.0192 1.0000
13.750 1.2815 0.04019 0.03474 0.0171 0.0189 1.0000
14.000 1.2852 0.04247 0.03712 0.0174 0.0187 1.0000
14.250 1.2875 0.04501 0.03974 0.0176 0.0185 1.0000
14.500 1.2882 0.04785 0.04268 0.0177 0.0184 1.0000
14.750 1.2869 0.05101 0.04596 0.0177 0.0182 1.0000
15.000 1.2834 0.05453 0.04962 0.0174 0.0182 1.0000
15.250 1.2772 0.05846 0.05371 0.0167 0.0181 1.0000
15.500 1.2690 0.06278 0.05820 0.0155 0.0181 1.0000
15.750 1.2589 0.06743 0.06302 0.0137 0.0180 1.0000
16.000 1.2477 0.07242 0.06818 0.0115 0.0180 1.0000
16.250 1.2347 0.07790 0.07383 0.0088 0.0180 1.0000
16.500 1.2200 0.08389 0.07998 0.0057 0.0180 1.0000
16.750 1.2050 0.09023 0.08650 0.0020 0.0181 1.0000
17.000 1.1900 0.09689 0.09331 -0.0021 0.0181 1.0000
17.250 1.1734 0.10420 0.10078 -0.0067 0.0181 1.0000
17.500 1.1548 0.11233 0.10908 -0.0121 0.0182 1.0000
17.750 1.1312 0.12207 0.11901 -0.0187 0.0183 1.0000
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