NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 500,000 Max Cl/Cd: 49.11 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nplx-il-500000.txt Download as CSV file: xf-nplx-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
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 -0.4773 0.08788 0.08549 -0.0332 1.0000 0.0278
-10.000 -0.4899 0.08091 0.07853 -0.0360 1.0000 0.0279
-9.750 -0.8382 0.04431 0.04065 -0.0471 1.0000 0.0168
-9.500 -0.8369 0.04224 0.03845 -0.0449 1.0000 0.0163
-9.250 -0.8449 0.03904 0.03508 -0.0423 1.0000 0.0160
-9.000 -0.8526 0.03528 0.03103 -0.0393 1.0000 0.0157
-8.750 -0.8552 0.03159 0.02699 -0.0364 1.0000 0.0153
-8.500 -0.8538 0.02780 0.02276 -0.0336 1.0000 0.0150
-8.250 -0.8449 0.02504 0.01965 -0.0314 1.0000 0.0148
-8.000 -0.8316 0.02312 0.01747 -0.0295 1.0000 0.0148
-7.750 -0.8162 0.02161 0.01578 -0.0278 1.0000 0.0149
-7.500 -0.7997 0.02038 0.01439 -0.0261 1.0000 0.0150
-7.250 -0.7825 0.01932 0.01322 -0.0246 1.0000 0.0152
-7.000 -0.7647 0.01840 0.01220 -0.0231 1.0000 0.0156
-6.750 -0.7466 0.01758 0.01129 -0.0216 1.0000 0.0159
-6.500 -0.7281 0.01687 0.01049 -0.0202 1.0000 0.0162
-6.250 -0.7025 0.01601 0.00955 -0.0203 0.9991 0.0166
-6.000 -0.6704 0.01509 0.00862 -0.0219 0.9970 0.0174
-5.750 -0.6363 0.01457 0.00809 -0.0237 0.9949 0.0185
-5.500 -0.6027 0.01404 0.00751 -0.0253 0.9927 0.0198
-5.250 -0.5704 0.01335 0.00682 -0.0267 0.9897 0.0218
-5.000 -0.5359 0.01291 0.00637 -0.0284 0.9872 0.0254
-4.750 -0.5008 0.01249 0.00598 -0.0303 0.9852 0.0318
-4.500 -0.4655 0.01224 0.00575 -0.0322 0.9833 0.0364
-4.250 -0.4352 0.01184 0.00538 -0.0330 0.9791 0.0413
-4.000 -0.4009 0.01160 0.00512 -0.0346 0.9763 0.0461
-3.750 -0.3656 0.01120 0.00476 -0.0364 0.9741 0.0524
-3.500 -0.3291 0.01085 0.00444 -0.0385 0.9726 0.0601
-3.250 -0.3000 0.01052 0.00416 -0.0389 0.9674 0.0705
-3.000 -0.2667 0.01017 0.00389 -0.0403 0.9642 0.0904
-2.750 -0.2319 0.00965 0.00359 -0.0421 0.9620 0.1374
-2.500 -0.2016 0.00777 0.00302 -0.0443 0.9601 0.4731
-2.250 -0.1698 0.00762 0.00299 -0.0451 0.9563 0.5259
-2.000 -0.1376 0.00755 0.00295 -0.0459 0.9521 0.5489
-1.750 -0.1013 0.00747 0.00289 -0.0476 0.9496 0.5646
-1.500 -0.0618 0.00736 0.00279 -0.0498 0.9471 0.5777
-1.250 -0.0253 0.00727 0.00268 -0.0514 0.9426 0.5893
-1.000 0.0070 0.00721 0.00263 -0.0520 0.9356 0.6017
-0.750 0.0434 0.00712 0.00257 -0.0536 0.9311 0.6118
-0.500 0.0736 0.00708 0.00251 -0.0539 0.9230 0.6174
-0.250 0.1086 0.00696 0.00239 -0.0551 0.9152 0.6227
0.000 0.1380 0.00690 0.00233 -0.0550 0.9022 0.6284
0.250 0.1672 0.00690 0.00229 -0.0550 0.8888 0.6349
0.500 0.1956 0.00684 0.00225 -0.0548 0.8742 0.6401
0.750 0.2238 0.00682 0.00220 -0.0545 0.8577 0.6439
1.000 0.2514 0.00684 0.00213 -0.0541 0.8354 0.6482
1.250 0.2777 0.00688 0.00209 -0.0534 0.8098 0.6524
1.500 0.3037 0.00692 0.00209 -0.0527 0.7840 0.6564
1.750 0.3286 0.00700 0.00208 -0.0517 0.7478 0.6608
2.000 0.3521 0.00717 0.00207 -0.0505 0.6943 0.6656
2.250 0.3674 0.00779 0.00211 -0.0477 0.5524 0.6701
2.500 0.3826 0.00870 0.00237 -0.0453 0.3932 0.6747
2.750 0.4026 0.00942 0.00260 -0.0440 0.2767 0.6801
3.000 0.4210 0.01039 0.00291 -0.0425 0.1252 0.6856
3.250 0.4448 0.01082 0.00320 -0.0417 0.0876 0.6912
3.500 0.4694 0.01123 0.00352 -0.0410 0.0692 0.6977
3.750 0.4951 0.01147 0.00376 -0.0405 0.0617 0.7037
4.000 0.5201 0.01180 0.00410 -0.0398 0.0562 0.7102
4.250 0.5459 0.01205 0.00437 -0.0394 0.0532 0.7173
4.500 0.5710 0.01233 0.00468 -0.0387 0.0506 0.7241
5.000 0.6187 0.01323 0.00567 -0.0370 0.0469 0.7394
5.250 0.6436 0.01358 0.00607 -0.0364 0.0457 0.7483
5.500 0.6681 0.01390 0.00646 -0.0357 0.0443 0.7570
5.750 0.6927 0.01425 0.00685 -0.0350 0.0429 0.7666
6.000 0.7168 0.01466 0.00731 -0.0342 0.0418 0.7769
6.250 0.7399 0.01520 0.00791 -0.0333 0.0408 0.7876
6.500 0.7617 0.01625 0.00902 -0.0322 0.0396 0.7994
6.750 0.7851 0.01711 0.00999 -0.0314 0.0390 0.8127
7.000 0.8091 0.01763 0.01063 -0.0306 0.0385 0.8280
7.250 0.8324 0.01824 0.01138 -0.0296 0.0380 0.8464
7.500 0.8548 0.01886 0.01216 -0.0284 0.0374 0.8710
7.750 0.8745 0.01936 0.01285 -0.0267 0.0366 0.9088
8.000 0.9046 0.02006 0.01371 -0.0272 0.0358 1.0000
8.250 0.9294 0.02098 0.01468 -0.0268 0.0352 1.0000
8.500 0.9534 0.02194 0.01572 -0.0263 0.0346 1.0000
8.750 0.9767 0.02293 0.01679 -0.0257 0.0340 1.0000
9.000 0.9994 0.02403 0.01796 -0.0251 0.0335 1.0000
9.250 1.0210 0.02545 0.01947 -0.0244 0.0331 1.0000
9.500 1.0402 0.02763 0.02182 -0.0234 0.0326 1.0000
9.750 1.0504 0.03145 0.02603 -0.0215 0.0319 1.0000
10.000 1.0685 0.03200 0.02677 -0.0200 0.0314 1.0000
10.250 1.0834 0.03349 0.02850 -0.0183 0.0307 1.0000
10.500 1.0938 0.03572 0.03102 -0.0163 0.0301 1.0000
10.750 1.0996 0.03840 0.03401 -0.0138 0.0295 1.0000
11.000 1.0985 0.04179 0.03772 -0.0109 0.0292 1.0000
11.250 1.0881 0.04587 0.04215 -0.0073 0.0289 1.0000
11.500 1.0662 0.05026 0.04686 -0.0029 0.0288 1.0000
11.750 1.0292 0.05518 0.05207 0.0022 0.0289 1.0000
12.000 0.9800 0.06187 0.05905 0.0046 0.0294 1.0000
12.250 0.9347 0.06942 0.06682 0.0028 0.0300 1.0000
12.500 0.8847 0.08046 0.07803 -0.0046 0.0306 1.0000
12.750 0.8454 0.09365 0.09127 -0.0146 0.0317 1.0000
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Polar data table (+)
Polar graphs
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