NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 100,000 Max Cl/Cd: 41.07 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9660-il-100000-n5.txt Download as CSV file: xf-npl9660-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6179 0.09341 0.08816 -0.0114 1.0000 0.0320
-10.000 -0.6312 0.08410 0.07887 -0.0190 1.0000 0.0314
-9.750 -0.6566 0.07475 0.06941 -0.0267 1.0000 0.0307
-9.500 -0.6843 0.06795 0.06244 -0.0296 1.0000 0.0302
-9.250 -0.7074 0.06227 0.05650 -0.0297 1.0000 0.0298
-9.000 -0.7208 0.05691 0.05080 -0.0290 1.0000 0.0296
-8.750 -0.7242 0.05259 0.04616 -0.0279 1.0000 0.0296
-8.500 -0.7217 0.04893 0.04219 -0.0267 1.0000 0.0297
-8.250 -0.7151 0.04572 0.03868 -0.0254 1.0000 0.0299
-8.000 -0.7060 0.04279 0.03545 -0.0240 1.0000 0.0302
-7.750 -0.6951 0.04006 0.03240 -0.0224 1.0000 0.0306
-7.500 -0.6828 0.03745 0.02945 -0.0208 1.0000 0.0311
-7.250 -0.6695 0.03489 0.02654 -0.0190 1.0000 0.0319
-7.000 -0.6554 0.03222 0.02336 -0.0169 1.0000 0.0333
-6.750 -0.6388 0.03066 0.02160 -0.0154 1.0000 0.0347
-6.500 -0.6210 0.02960 0.02044 -0.0140 1.0000 0.0363
-6.250 -0.6025 0.02782 0.01826 -0.0123 1.0000 0.0390
-6.000 -0.5835 0.02672 0.01711 -0.0110 1.0000 0.0407
-5.750 -0.5639 0.02568 0.01596 -0.0097 1.0000 0.0433
-5.500 -0.5437 0.02458 0.01468 -0.0083 1.0000 0.0463
-5.250 -0.5241 0.02389 0.01399 -0.0071 1.0000 0.0492
-5.000 -0.5033 0.02302 0.01297 -0.0059 1.0000 0.0521
-4.750 -0.4828 0.02215 0.01205 -0.0047 1.0000 0.0540
-4.500 -0.4629 0.02153 0.01148 -0.0036 1.0000 0.0568
-4.250 -0.4424 0.02103 0.01092 -0.0024 1.0000 0.0605
-4.000 -0.4200 0.02040 0.01028 -0.0017 0.9992 0.0635
-3.750 -0.3833 0.01972 0.00966 -0.0040 0.9933 0.0675
-3.500 -0.3466 0.01916 0.00906 -0.0061 0.9872 0.0712
-3.250 -0.3074 0.01855 0.00845 -0.0088 0.9824 0.0756
-3.000 -0.2702 0.01810 0.00800 -0.0110 0.9757 0.0824
-2.750 -0.2292 0.01760 0.00749 -0.0140 0.9708 0.0903
-2.500 -0.1931 0.01721 0.00708 -0.0159 0.9630 0.0998
-2.250 -0.1594 0.01668 0.00669 -0.0173 0.9542 0.1211
-2.000 -0.1395 0.01438 0.00640 -0.0169 0.9445 0.5262
-1.750 -0.1145 0.01390 0.00657 -0.0153 0.9346 0.6839
-1.500 -0.0895 0.01390 0.00687 -0.0132 0.9235 0.7652
-1.250 -0.0634 0.01409 0.00715 -0.0113 0.9122 0.8229
-1.000 -0.0353 0.01433 0.00738 -0.0098 0.9018 0.8669
-0.750 -0.0075 0.01461 0.00763 -0.0082 0.8893 0.9019
-0.500 0.0252 0.01472 0.00767 -0.0081 0.8759 0.9221
-0.250 0.0580 0.01464 0.00751 -0.0086 0.8620 0.9338
0.000 0.0923 0.01451 0.00730 -0.0095 0.8483 0.9430
0.250 0.1253 0.01436 0.00707 -0.0102 0.8337 0.9529
0.500 0.1589 0.01420 0.00684 -0.0110 0.8165 0.9619
0.750 0.1961 0.01402 0.00658 -0.0126 0.7970 0.9689
1.000 0.2349 0.01386 0.00635 -0.0145 0.7752 0.9746
1.250 0.2720 0.01373 0.00613 -0.0161 0.7529 0.9811
1.500 0.3105 0.01362 0.00593 -0.0180 0.7301 0.9864
1.750 0.3466 0.01357 0.00576 -0.0195 0.7054 0.9925
2.000 0.3829 0.01357 0.00565 -0.0211 0.6756 0.9988
2.250 0.4079 0.01363 0.00558 -0.0205 0.6487 1.0000
2.500 0.4308 0.01372 0.00559 -0.0196 0.6230 1.0000
2.750 0.4536 0.01383 0.00560 -0.0186 0.5981 1.0000
3.000 0.4763 0.01397 0.00563 -0.0176 0.5737 1.0000
3.250 0.4991 0.01413 0.00571 -0.0167 0.5481 1.0000
3.500 0.5216 0.01431 0.00582 -0.0158 0.5226 1.0000
3.750 0.5440 0.01452 0.00594 -0.0148 0.4983 1.0000
4.000 0.5664 0.01474 0.00611 -0.0139 0.4729 1.0000
4.250 0.5883 0.01499 0.00631 -0.0128 0.4464 1.0000
4.500 0.6100 0.01527 0.00652 -0.0118 0.4175 1.0000
4.750 0.6311 0.01560 0.00674 -0.0107 0.3866 1.0000
5.000 0.6519 0.01597 0.00701 -0.0095 0.3546 1.0000
5.250 0.6725 0.01638 0.00734 -0.0083 0.3239 1.0000
5.500 0.6925 0.01686 0.00770 -0.0071 0.2948 1.0000
5.750 0.7125 0.01737 0.00811 -0.0060 0.2673 1.0000
6.000 0.7320 0.01796 0.00855 -0.0048 0.2463 1.0000
6.250 0.7527 0.01851 0.00909 -0.0037 0.2272 1.0000
6.500 0.7736 0.01909 0.00963 -0.0028 0.2107 1.0000
6.750 0.7943 0.01970 0.01020 -0.0019 0.1959 1.0000
7.000 0.8152 0.02032 0.01080 -0.0010 0.1806 1.0000
7.250 0.8363 0.02092 0.01138 -0.0003 0.1643 1.0000
7.500 0.8575 0.02152 0.01200 0.0004 0.1478 1.0000
7.750 0.8786 0.02214 0.01264 0.0011 0.1322 1.0000
8.000 0.8993 0.02283 0.01332 0.0018 0.1181 1.0000
8.250 0.9198 0.02355 0.01408 0.0026 0.1046 1.0000
8.500 0.9393 0.02438 0.01493 0.0034 0.0918 1.0000
8.750 0.9588 0.02525 0.01584 0.0042 0.0781 1.0000
9.000 0.9760 0.02631 0.01685 0.0052 0.0686 1.0000
9.250 0.9920 0.02749 0.01806 0.0063 0.0616 1.0000
9.500 1.0070 0.02874 0.01934 0.0075 0.0567 1.0000
9.750 1.0218 0.03001 0.02073 0.0088 0.0526 1.0000
10.000 1.0355 0.03133 0.02213 0.0101 0.0495 1.0000
10.250 1.0482 0.03265 0.02354 0.0114 0.0465 1.0000
10.500 1.0599 0.03406 0.02505 0.0127 0.0441 1.0000
10.750 1.0694 0.03549 0.02660 0.0143 0.0420 1.0000
11.000 1.0770 0.03701 0.02816 0.0158 0.0405 1.0000
11.250 1.0851 0.03872 0.03004 0.0171 0.0389 1.0000
11.500 1.0925 0.04054 0.03204 0.0184 0.0376 1.0000
11.750 1.0987 0.04248 0.03411 0.0194 0.0366 1.0000
12.000 1.1041 0.04452 0.03625 0.0203 0.0358 1.0000
12.250 1.1093 0.04666 0.03845 0.0211 0.0351 1.0000
12.500 1.1125 0.04919 0.04116 0.0217 0.0345 1.0000
12.750 1.1126 0.05211 0.04436 0.0220 0.0340 1.0000
13.000 1.1103 0.05538 0.04788 0.0219 0.0335 1.0000
13.250 1.1053 0.05904 0.05178 0.0214 0.0330 1.0000
13.500 1.0979 0.06314 0.05612 0.0202 0.0326 1.0000
13.750 1.0881 0.06775 0.06096 0.0185 0.0323 1.0000
14.000 1.0755 0.07303 0.06647 0.0160 0.0320 1.0000
14.250 1.0592 0.07918 0.07284 0.0126 0.0318 1.0000
14.500 1.0374 0.08673 0.08064 0.0081 0.0319 1.0000
14.750 1.0058 0.09678 0.09096 0.0017 0.0321 1.0000
15.000 0.9462 0.11456 0.10906 -0.0101 0.0331 1.0000
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