NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.55 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nplx-il-1000000-n5.txt Download as CSV file: xf-nplx-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9875 0.08264 0.08004 -0.0347 1.0000 0.0061
-15.250 -1.0247 0.07030 0.06747 -0.0425 1.0000 0.0060
-15.000 -1.0522 0.06202 0.05901 -0.0473 1.0000 0.0060
-14.750 -1.0649 0.05689 0.05375 -0.0499 1.0000 0.0060
-14.500 -1.0783 0.05198 0.04870 -0.0521 1.0000 0.0060
-14.250 -1.0878 0.04789 0.04448 -0.0536 1.0000 0.0060
-14.000 -1.0925 0.04457 0.04104 -0.0546 1.0000 0.0060
-13.750 -1.1029 0.04076 0.03707 -0.0555 1.0000 0.0060
-13.500 -1.1031 0.03828 0.03448 -0.0557 1.0000 0.0059
-13.250 -1.1114 0.03507 0.03111 -0.0557 1.0000 0.0060
-13.000 -1.1089 0.03312 0.02906 -0.0552 1.0000 0.0060
-12.750 -1.1126 0.03075 0.02654 -0.0544 1.0000 0.0060
-12.500 -1.1101 0.02914 0.02483 -0.0532 1.0000 0.0060
-12.250 -1.1101 0.02762 0.02320 -0.0514 1.0000 0.0060
-12.000 -1.1123 0.02640 0.02189 -0.0485 1.0000 0.0060
-11.750 -1.1129 0.02522 0.02060 -0.0452 1.0000 0.0060
-11.500 -1.1038 0.02425 0.01954 -0.0432 1.0000 0.0060
-11.250 -1.0949 0.02317 0.01837 -0.0411 1.0000 0.0061
-11.000 -1.0839 0.02218 0.01728 -0.0392 1.0000 0.0061
-10.750 -1.0712 0.02128 0.01629 -0.0374 1.0000 0.0061
-10.500 -1.0572 0.02042 0.01535 -0.0357 1.0000 0.0062
-10.250 -1.0421 0.01964 0.01450 -0.0341 1.0000 0.0062
-10.000 -1.0189 0.01883 0.01361 -0.0342 0.9994 0.0062
-9.750 -0.9916 0.01805 0.01276 -0.0350 0.9984 0.0062
-9.500 -0.9643 0.01725 0.01189 -0.0358 0.9971 0.0063
-9.250 -0.9361 0.01659 0.01117 -0.0367 0.9959 0.0064
-9.000 -0.9074 0.01592 0.01044 -0.0376 0.9947 0.0065
-8.750 -0.8788 0.01534 0.00981 -0.0384 0.9934 0.0065
-8.500 -0.8519 0.01476 0.00918 -0.0388 0.9916 0.0066
-8.250 -0.8240 0.01424 0.00862 -0.0393 0.9898 0.0067
-8.000 -0.7953 0.01374 0.00808 -0.0400 0.9881 0.0068
-7.750 -0.7658 0.01326 0.00757 -0.0408 0.9866 0.0069
-7.500 -0.7354 0.01281 0.00709 -0.0418 0.9852 0.0071
-7.250 -0.7042 0.01240 0.00664 -0.0429 0.9841 0.0072
-7.000 -0.6781 0.01201 0.00623 -0.0429 0.9810 0.0074
-6.750 -0.6500 0.01163 0.00583 -0.0432 0.9781 0.0076
-6.500 -0.6201 0.01128 0.00546 -0.0439 0.9759 0.0077
-6.250 -0.5894 0.01094 0.00510 -0.0448 0.9741 0.0080
-5.750 -0.5320 0.01029 0.00443 -0.0456 0.9682 0.0089
-5.500 -0.5032 0.01000 0.00414 -0.0460 0.9643 0.0095
-5.250 -0.4716 0.00971 0.00386 -0.0470 0.9616 0.0105
-5.000 -0.4381 0.00942 0.00358 -0.0484 0.9597 0.0130
-4.750 -0.4083 0.00915 0.00334 -0.0490 0.9553 0.0169
-4.500 -0.3766 0.00891 0.00312 -0.0500 0.9511 0.0199
-4.250 -0.3430 0.00868 0.00291 -0.0514 0.9476 0.0233
-4.000 -0.3093 0.00846 0.00272 -0.0528 0.9436 0.0270
-3.750 -0.2778 0.00828 0.00254 -0.0537 0.9370 0.0302
-3.500 -0.2444 0.00808 0.00236 -0.0550 0.9310 0.0346
-3.250 -0.2139 0.00790 0.00220 -0.0556 0.9232 0.0404
-3.000 -0.1830 0.00773 0.00205 -0.0563 0.9157 0.0477
-2.750 -0.1540 0.00758 0.00191 -0.0566 0.9063 0.0569
-2.500 -0.1253 0.00742 0.00179 -0.0567 0.8940 0.0719
-2.250 -0.0977 0.00729 0.00167 -0.0567 0.8776 0.0877
-2.000 -0.0708 0.00715 0.00155 -0.0565 0.8613 0.1092
-1.750 -0.0451 0.00680 0.00140 -0.0562 0.8475 0.1797
-1.500 -0.0241 0.00560 0.00100 -0.0557 0.8336 0.4331
-1.000 0.0298 0.00546 0.00096 -0.0551 0.8089 0.4968
-0.750 0.0566 0.00546 0.00095 -0.0548 0.7923 0.5136
-0.500 0.0832 0.00548 0.00095 -0.0543 0.7743 0.5310
-0.250 0.1100 0.00553 0.00094 -0.0540 0.7550 0.5382
0.000 0.1362 0.00561 0.00093 -0.0534 0.7272 0.5419
0.250 0.1605 0.00577 0.00092 -0.0526 0.6770 0.5467
0.500 0.1814 0.00621 0.00097 -0.0510 0.5713 0.5520
0.750 0.2014 0.00685 0.00111 -0.0495 0.4364 0.5572
1.000 0.2244 0.00729 0.00123 -0.0486 0.3448 0.5649
1.250 0.2488 0.00766 0.00133 -0.0480 0.2741 0.5710
1.500 0.2724 0.00809 0.00145 -0.0472 0.1878 0.5744
1.750 0.2962 0.00854 0.00161 -0.0465 0.1081 0.5780
2.000 0.3228 0.00872 0.00171 -0.0462 0.0876 0.5816
2.250 0.3498 0.00887 0.00181 -0.0459 0.0759 0.5851
2.500 0.3767 0.00901 0.00190 -0.0457 0.0666 0.5883
2.750 0.4035 0.00915 0.00201 -0.0454 0.0570 0.5921
3.000 0.4303 0.00931 0.00213 -0.0451 0.0484 0.5961
3.250 0.4571 0.00947 0.00225 -0.0448 0.0423 0.6002
3.750 0.5107 0.00976 0.00253 -0.0442 0.0364 0.6086
4.000 0.5373 0.00992 0.00269 -0.0439 0.0345 0.6136
4.250 0.5639 0.01011 0.00287 -0.0436 0.0328 0.6184
4.500 0.5904 0.01028 0.00306 -0.0432 0.0318 0.6231
4.750 0.6170 0.01044 0.00324 -0.0429 0.0312 0.6282
5.000 0.6434 0.01061 0.00344 -0.0425 0.0305 0.6334
5.250 0.6698 0.01079 0.00364 -0.0422 0.0297 0.6382
5.500 0.6959 0.01098 0.00385 -0.0418 0.0288 0.6439
5.750 0.7219 0.01120 0.00408 -0.0414 0.0281 0.6496
6.000 0.7477 0.01143 0.00434 -0.0409 0.0274 0.6554
6.250 0.7729 0.01172 0.00466 -0.0403 0.0266 0.6623
6.500 0.7979 0.01205 0.00503 -0.0397 0.0260 0.6690
6.750 0.8235 0.01227 0.00530 -0.0393 0.0258 0.6763
7.000 0.8490 0.01251 0.00558 -0.0388 0.0255 0.6834
7.250 0.8742 0.01276 0.00589 -0.0382 0.0252 0.6907
7.500 0.8993 0.01304 0.00621 -0.0377 0.0248 0.6985
7.750 0.9242 0.01332 0.00655 -0.0371 0.0244 0.7061
8.000 0.9489 0.01361 0.00688 -0.0365 0.0240 0.7143
8.250 0.9736 0.01390 0.00722 -0.0359 0.0235 0.7224
8.500 0.9982 0.01418 0.00755 -0.0353 0.0231 0.7315
8.750 1.0223 0.01449 0.00792 -0.0346 0.0227 0.7410
9.000 1.0462 0.01483 0.00831 -0.0339 0.0224 0.7504
9.250 1.0696 0.01520 0.00874 -0.0331 0.0220 0.7610
9.500 1.0921 0.01565 0.00926 -0.0322 0.0216 0.7724
9.750 1.1131 0.01625 0.00994 -0.0310 0.0210 0.7857
10.000 1.1362 0.01656 0.01036 -0.0302 0.0209 0.8014
10.250 1.1594 0.01681 0.01070 -0.0294 0.0206 0.8211
10.500 1.1808 0.01715 0.01118 -0.0283 0.0204 0.8479
10.750 1.2004 0.01746 0.01165 -0.0267 0.0202 0.8887
11.000 1.2241 0.01776 0.01214 -0.0261 0.0199 1.0000
11.250 1.2457 0.01824 0.01267 -0.0251 0.0196 1.0000
11.500 1.2670 0.01872 0.01320 -0.0241 0.0193 1.0000
11.750 1.2883 0.01917 0.01369 -0.0231 0.0190 1.0000
12.000 1.3089 0.01966 0.01423 -0.0220 0.0187 1.0000
12.250 1.3299 0.02007 0.01468 -0.0210 0.0184 1.0000
12.500 1.3505 0.02048 0.01511 -0.0199 0.0180 1.0000
12.750 1.3707 0.02089 0.01552 -0.0188 0.0176 1.0000
13.000 1.3876 0.02156 0.01625 -0.0173 0.0173 1.0000
13.250 1.4007 0.02234 0.01709 -0.0151 0.0169 1.0000
13.500 1.4174 0.02278 0.01759 -0.0134 0.0168 1.0000
13.750 1.4305 0.02345 0.01835 -0.0112 0.0166 1.0000
14.000 1.4442 0.02407 0.01904 -0.0092 0.0164 1.0000
14.250 1.4577 0.02470 0.01973 -0.0073 0.0162 1.0000
14.500 1.4706 0.02537 0.02047 -0.0053 0.0159 1.0000
14.750 1.4815 0.02618 0.02136 -0.0032 0.0157 1.0000
15.000 1.4924 0.02698 0.02224 -0.0012 0.0154 1.0000
15.250 1.5015 0.02794 0.02328 0.0008 0.0153 1.0000
15.500 1.5103 0.02893 0.02435 0.0028 0.0151 1.0000
15.750 1.5201 0.02987 0.02535 0.0044 0.0148 1.0000
16.000 1.5284 0.03095 0.02649 0.0061 0.0146 1.0000
16.250 1.5350 0.03221 0.02783 0.0078 0.0144 1.0000
16.500 1.5407 0.03358 0.02927 0.0093 0.0142 1.0000
16.750 1.5449 0.03515 0.03092 0.0107 0.0140 1.0000
17.000 1.5468 0.03699 0.03285 0.0119 0.0138 1.0000
17.250 1.5463 0.03916 0.03512 0.0130 0.0136 1.0000
17.500 1.5441 0.04162 0.03769 0.0137 0.0135 1.0000
17.750 1.5397 0.04447 0.04066 0.0140 0.0134 1.0000
18.000 1.5356 0.04749 0.04381 0.0140 0.0133 1.0000
18.250 1.5288 0.05104 0.04749 0.0133 0.0133 1.0000
18.500 1.5173 0.05554 0.05213 0.0119 0.0132 1.0000
18.750 1.5033 0.06087 0.05762 0.0094 0.0131 1.0000
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