NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 100,000 Max Cl/Cd: 40.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9627-il-100000-n5.txt Download as CSV file: xf-npl9627-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9627 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7367 0.09028 0.08455 -0.0211 1.0000 0.0272
-12.250 -0.7624 0.08066 0.07481 -0.0283 1.0000 0.0269
-12.000 -0.7883 0.07215 0.06612 -0.0350 1.0000 0.0267
-11.750 -0.8121 0.06542 0.05917 -0.0397 1.0000 0.0265
-11.500 -0.8334 0.06020 0.05371 -0.0421 1.0000 0.0265
-11.250 -0.8525 0.05603 0.04929 -0.0422 1.0000 0.0265
-11.000 -0.8693 0.05258 0.04555 -0.0405 1.0000 0.0267
-10.750 -0.8827 0.04934 0.04193 -0.0380 1.0000 0.0270
-10.500 -0.8863 0.04646 0.03872 -0.0359 1.0000 0.0275
-10.250 -0.8765 0.04473 0.03694 -0.0346 1.0000 0.0281
-10.000 -0.8681 0.04280 0.03485 -0.0331 1.0000 0.0290
-9.750 -0.8606 0.04059 0.03232 -0.0313 1.0000 0.0300
-9.500 -0.8531 0.03816 0.02939 -0.0292 1.0000 0.0312
-9.250 -0.8375 0.03665 0.02785 -0.0281 1.0000 0.0323
-9.000 -0.8218 0.03520 0.02627 -0.0268 1.0000 0.0338
-8.750 -0.8071 0.03346 0.02413 -0.0251 1.0000 0.0356
-8.500 -0.7890 0.03211 0.02282 -0.0241 1.0000 0.0371
-8.250 -0.7708 0.03078 0.02135 -0.0228 1.0000 0.0389
-8.000 -0.7518 0.02933 0.01965 -0.0214 1.0000 0.0404
-7.750 -0.7328 0.02797 0.01833 -0.0201 1.0000 0.0417
-7.500 -0.7142 0.02680 0.01713 -0.0187 1.0000 0.0432
-7.250 -0.6957 0.02570 0.01595 -0.0172 1.0000 0.0450
-7.000 -0.6782 0.02465 0.01488 -0.0155 1.0000 0.0468
-6.750 -0.6611 0.02372 0.01396 -0.0138 1.0000 0.0490
-6.500 -0.6430 0.02293 0.01306 -0.0121 1.0000 0.0520
-6.250 -0.6261 0.02209 0.01227 -0.0105 1.0000 0.0555
-6.000 -0.6082 0.02136 0.01152 -0.0089 1.0000 0.0604
-5.750 -0.5900 0.02069 0.01081 -0.0073 1.0000 0.0660
-5.500 -0.5722 0.01995 0.01010 -0.0057 1.0000 0.0715
-5.250 -0.5537 0.01925 0.00943 -0.0042 1.0000 0.0794
-5.000 -0.5351 0.01852 0.00880 -0.0027 1.0000 0.0936
-4.750 -0.5169 0.01768 0.00822 -0.0013 1.0000 0.1313
-4.500 -0.4984 0.01692 0.00781 -0.0001 1.0000 0.1960
-4.250 -0.4789 0.01642 0.00757 0.0011 1.0000 0.2500
-4.000 -0.4517 0.01607 0.00736 0.0008 0.9971 0.2969
-3.750 -0.4145 0.01571 0.00722 -0.0015 0.9897 0.3537
-3.500 -0.3774 0.01539 0.00709 -0.0037 0.9817 0.4114
-3.250 -0.3421 0.01503 0.00693 -0.0053 0.9725 0.4594
-3.000 -0.3042 0.01471 0.00675 -0.0074 0.9642 0.4989
-2.750 -0.2674 0.01442 0.00657 -0.0091 0.9544 0.5331
-2.500 -0.2325 0.01413 0.00643 -0.0103 0.9437 0.5724
-2.250 -0.1964 0.01386 0.00631 -0.0116 0.9341 0.6186
-2.000 -0.1642 0.01364 0.00625 -0.0119 0.9216 0.6679
-1.750 -0.1320 0.01348 0.00624 -0.0121 0.9088 0.7171
-1.500 -0.0981 0.01339 0.00623 -0.0125 0.8964 0.7631
-1.250 -0.0624 0.01334 0.00624 -0.0131 0.8841 0.8033
-1.000 -0.0284 0.01335 0.00625 -0.0135 0.8686 0.8366
-0.750 0.0058 0.01338 0.00624 -0.0140 0.8524 0.8652
-0.500 0.0425 0.01341 0.00622 -0.0149 0.8349 0.8877
-0.250 0.0789 0.01345 0.00617 -0.0159 0.8161 0.9072
0.000 0.1151 0.01349 0.00612 -0.0169 0.7966 0.9241
0.250 0.1515 0.01354 0.00608 -0.0181 0.7768 0.9391
0.500 0.1883 0.01360 0.00604 -0.0195 0.7557 0.9526
0.750 0.2284 0.01366 0.00600 -0.0216 0.7335 0.9638
1.000 0.2687 0.01370 0.00593 -0.0239 0.7113 0.9736
1.250 0.3076 0.01375 0.00588 -0.0260 0.6899 0.9834
1.500 0.3465 0.01381 0.00584 -0.0282 0.6696 0.9926
1.750 0.3859 0.01385 0.00582 -0.0306 0.6487 1.0000
2.000 0.4089 0.01393 0.00582 -0.0297 0.6295 1.0000
2.250 0.4317 0.01403 0.00584 -0.0287 0.6088 1.0000
2.500 0.4542 0.01415 0.00587 -0.0276 0.5866 1.0000
2.750 0.4764 0.01429 0.00589 -0.0265 0.5630 1.0000
3.000 0.4983 0.01444 0.00597 -0.0253 0.5364 1.0000
3.250 0.5200 0.01463 0.00603 -0.0241 0.5102 1.0000
3.500 0.5416 0.01482 0.00613 -0.0228 0.4814 1.0000
3.750 0.5628 0.01505 0.00623 -0.0216 0.4506 1.0000
4.000 0.5839 0.01531 0.00638 -0.0203 0.4213 1.0000
4.250 0.6055 0.01557 0.00658 -0.0191 0.3954 1.0000
4.500 0.6267 0.01589 0.00679 -0.0179 0.3682 1.0000
4.750 0.6475 0.01624 0.00705 -0.0167 0.3382 1.0000
5.000 0.6678 0.01665 0.00733 -0.0154 0.3068 1.0000
5.250 0.6877 0.01713 0.00767 -0.0140 0.2735 1.0000
5.500 0.7069 0.01768 0.00808 -0.0126 0.2392 1.0000
5.750 0.7257 0.01831 0.00854 -0.0112 0.2040 1.0000
6.000 0.7439 0.01903 0.00908 -0.0097 0.1721 1.0000
6.250 0.7622 0.01976 0.00968 -0.0083 0.1506 1.0000
6.500 0.7808 0.02049 0.01033 -0.0069 0.1370 1.0000
6.750 0.7993 0.02123 0.01101 -0.0055 0.1281 1.0000
7.000 0.8186 0.02191 0.01170 -0.0041 0.1211 1.0000
7.250 0.8370 0.02266 0.01243 -0.0028 0.1152 1.0000
7.500 0.8560 0.02339 0.01319 -0.0015 0.1100 1.0000
7.750 0.8750 0.02413 0.01394 -0.0002 0.1049 1.0000
8.000 0.8928 0.02499 0.01477 0.0011 0.1006 1.0000
8.250 0.9122 0.02574 0.01561 0.0022 0.0963 1.0000
8.500 0.9305 0.02659 0.01646 0.0034 0.0925 1.0000
8.750 0.9484 0.02756 0.01743 0.0046 0.0893 1.0000
9.000 0.9675 0.02845 0.01845 0.0058 0.0859 1.0000
9.250 0.9857 0.02941 0.01944 0.0069 0.0828 1.0000
9.500 1.0035 0.03053 0.02051 0.0079 0.0802 1.0000
9.750 1.0220 0.03165 0.02180 0.0090 0.0777 1.0000
10.000 1.0399 0.03281 0.02309 0.0101 0.0751 1.0000
10.250 1.0572 0.03397 0.02431 0.0112 0.0727 1.0000
10.500 1.0761 0.03531 0.02557 0.0119 0.0706 1.0000
10.750 1.0901 0.03672 0.02726 0.0133 0.0684 1.0000
11.000 1.1043 0.03821 0.02896 0.0146 0.0664 1.0000
11.250 1.1183 0.03971 0.03060 0.0158 0.0647 1.0000
11.500 1.1326 0.04118 0.03212 0.0169 0.0633 1.0000
11.750 1.1478 0.04284 0.03380 0.0178 0.0619 1.0000
12.000 1.1483 0.04479 0.03611 0.0203 0.0605 1.0000
12.250 1.1486 0.04683 0.03843 0.0225 0.0592 1.0000
12.500 1.1486 0.04896 0.04079 0.0243 0.0581 1.0000
12.750 1.1483 0.05119 0.04321 0.0258 0.0571 1.0000
13.000 1.1487 0.05342 0.04559 0.0268 0.0562 1.0000
13.250 1.1507 0.05561 0.04787 0.0276 0.0554 1.0000
13.500 1.1539 0.05790 0.05021 0.0281 0.0546 1.0000
13.750 1.1334 0.06222 0.05489 0.0280 0.0541 1.0000
14.000 1.1105 0.06735 0.06034 0.0267 0.0537 1.0000
14.250 1.0841 0.07353 0.06682 0.0240 0.0534 1.0000
14.500 1.0520 0.08124 0.07482 0.0198 0.0533 1.0000
14.750 1.0104 0.09152 0.08536 0.0133 0.0535 1.0000
15.000 0.9448 0.10819 0.10229 0.0020 0.0541 1.0000
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