NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 500,000 Max Cl/Cd: 65.27 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9626-il-500000.txt Download as CSV file: xf-npl9626-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9626 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
------ -------- --------- --------- -------- -------- --------
-13.250 -1.0250 0.04949 0.04557 -0.0408 1.0000 0.0155
-13.000 -1.0453 0.04464 0.04043 -0.0414 1.0000 0.0154
-12.750 -1.0557 0.04135 0.03693 -0.0406 1.0000 0.0155
-12.500 -1.0619 0.03871 0.03409 -0.0390 1.0000 0.0155
-12.250 -1.0649 0.03648 0.03168 -0.0369 1.0000 0.0156
-12.000 -1.0648 0.03460 0.02964 -0.0343 1.0000 0.0156
-11.750 -1.0611 0.03289 0.02777 -0.0319 1.0000 0.0157
-11.500 -1.0525 0.03127 0.02598 -0.0300 1.0000 0.0159
-11.250 -1.0416 0.02972 0.02427 -0.0283 1.0000 0.0160
-11.000 -1.0289 0.02825 0.02264 -0.0267 1.0000 0.0162
-10.750 -1.0145 0.02687 0.02112 -0.0252 1.0000 0.0164
-10.500 -0.9989 0.02558 0.01970 -0.0237 1.0000 0.0166
-10.250 -0.9824 0.02436 0.01833 -0.0223 1.0000 0.0168
-10.000 -0.9651 0.02321 0.01705 -0.0209 1.0000 0.0171
-9.750 -0.9469 0.02222 0.01592 -0.0195 1.0000 0.0175
-9.500 -0.9282 0.02133 0.01490 -0.0181 1.0000 0.0179
-9.250 -0.9109 0.02032 0.01389 -0.0167 1.0000 0.0184
-9.000 -0.8916 0.01970 0.01325 -0.0154 1.0000 0.0189
-8.750 -0.8726 0.01905 0.01256 -0.0139 1.0000 0.0196
-8.500 -0.8539 0.01838 0.01181 -0.0123 1.0000 0.0204
-8.250 -0.8354 0.01770 0.01103 -0.0107 1.0000 0.0213
-8.000 -0.8182 0.01697 0.01032 -0.0089 1.0000 0.0222
-7.750 -0.7992 0.01648 0.00981 -0.0074 1.0000 0.0233
-7.500 -0.7799 0.01603 0.00929 -0.0058 1.0000 0.0244
-7.250 -0.7631 0.01534 0.00859 -0.0038 1.0000 0.0256
-7.000 -0.7445 0.01488 0.00812 -0.0022 1.0000 0.0267
-6.750 -0.7253 0.01447 0.00769 -0.0006 1.0000 0.0281
-6.500 -0.7071 0.01396 0.00715 0.0011 1.0000 0.0297
-6.250 -0.6879 0.01355 0.00675 0.0026 1.0000 0.0315
-6.000 -0.6642 0.01326 0.00641 0.0033 0.9995 0.0336
-5.750 -0.6255 0.01271 0.00589 0.0007 0.9964 0.0367
-5.500 -0.5868 0.01233 0.00548 -0.0018 0.9939 0.0397
-5.250 -0.5521 0.01196 0.00514 -0.0034 0.9903 0.0429
-5.000 -0.5161 0.01161 0.00481 -0.0052 0.9870 0.0468
-4.750 -0.4786 0.01130 0.00451 -0.0074 0.9844 0.0522
-4.500 -0.4434 0.01092 0.00419 -0.0090 0.9806 0.0620
-4.250 -0.4082 0.01049 0.00386 -0.0107 0.9761 0.0804
-4.000 -0.3726 0.00986 0.00349 -0.0127 0.9723 0.1296
-3.750 -0.3435 0.00905 0.00315 -0.0134 0.9652 0.2324
-3.500 -0.3124 0.00851 0.00292 -0.0143 0.9584 0.3069
-3.250 -0.2841 0.00814 0.00276 -0.0144 0.9488 0.3606
-3.000 -0.2547 0.00783 0.00260 -0.0146 0.9397 0.4031
-2.750 -0.2283 0.00756 0.00245 -0.0141 0.9271 0.4408
-2.500 -0.2026 0.00728 0.00233 -0.0135 0.9133 0.4855
-2.250 -0.1774 0.00702 0.00222 -0.0128 0.8984 0.5341
-2.000 -0.1526 0.00677 0.00212 -0.0119 0.8816 0.5860
-1.750 -0.1282 0.00655 0.00205 -0.0108 0.8631 0.6397
-1.500 -0.1034 0.00640 0.00200 -0.0099 0.8436 0.6855
-1.250 -0.0786 0.00628 0.00196 -0.0089 0.8236 0.7271
-1.000 -0.0532 0.00621 0.00194 -0.0080 0.8021 0.7614
-0.750 -0.0275 0.00619 0.00193 -0.0072 0.7786 0.7899
-0.250 0.0241 0.00625 0.00192 -0.0056 0.7286 0.8356
0.000 0.0498 0.00634 0.00194 -0.0048 0.7027 0.8563
0.250 0.0758 0.00642 0.00198 -0.0041 0.6771 0.8754
0.500 0.1016 0.00654 0.00202 -0.0033 0.6524 0.8930
0.750 0.1277 0.00666 0.00208 -0.0026 0.6283 0.9089
1.000 0.1540 0.00682 0.00215 -0.0020 0.6025 0.9228
1.250 0.1818 0.00699 0.00223 -0.0017 0.5759 0.9342
1.500 0.2102 0.00716 0.00231 -0.0016 0.5532 0.9449
1.750 0.2386 0.00733 0.00240 -0.0015 0.5345 0.9554
2.000 0.2726 0.00752 0.00251 -0.0026 0.5166 0.9614
2.250 0.3042 0.00772 0.00261 -0.0033 0.4971 0.9694
2.500 0.3418 0.00790 0.00272 -0.0054 0.4772 0.9734
2.750 0.3806 0.00807 0.00282 -0.0077 0.4574 0.9768
3.000 0.4159 0.00824 0.00292 -0.0093 0.4381 0.9818
3.250 0.4541 0.00841 0.00302 -0.0116 0.4181 0.9850
3.500 0.4933 0.00857 0.00312 -0.0141 0.4008 0.9883
3.750 0.5309 0.00876 0.00324 -0.0163 0.3802 0.9924
4.000 0.5696 0.00893 0.00335 -0.0187 0.3530 0.9955
4.250 0.6077 0.00931 0.00345 -0.0212 0.2877 0.9985
4.500 0.6325 0.01059 0.00395 -0.0217 0.1360 1.0000
4.750 0.6514 0.01132 0.00437 -0.0204 0.0824 1.0000
5.000 0.6724 0.01166 0.00465 -0.0192 0.0715 1.0000
5.250 0.6932 0.01200 0.00496 -0.0179 0.0657 1.0000
5.500 0.7144 0.01227 0.00524 -0.0167 0.0624 1.0000
5.750 0.7347 0.01264 0.00558 -0.0154 0.0590 1.0000
6.000 0.7549 0.01301 0.00597 -0.0140 0.0563 1.0000
6.250 0.7756 0.01332 0.00631 -0.0127 0.0538 1.0000
6.500 0.7955 0.01372 0.00670 -0.0113 0.0513 1.0000
6.750 0.8131 0.01435 0.00733 -0.0095 0.0488 1.0000
7.000 0.8341 0.01466 0.00769 -0.0082 0.0470 1.0000
7.250 0.8544 0.01506 0.00810 -0.0069 0.0449 1.0000
7.500 0.8730 0.01561 0.00864 -0.0054 0.0430 1.0000
7.750 0.8897 0.01637 0.00943 -0.0036 0.0412 1.0000
8.000 0.9109 0.01673 0.00985 -0.0024 0.0398 1.0000
8.250 0.9317 0.01718 0.01032 -0.0013 0.0383 1.0000
8.500 0.9520 0.01767 0.01082 -0.0002 0.0369 1.0000
8.750 0.9672 0.01873 0.01186 0.0016 0.0355 1.0000
9.000 0.9888 0.01915 0.01235 0.0026 0.0346 1.0000
9.250 1.0097 0.01964 0.01291 0.0036 0.0334 1.0000
9.500 1.0302 0.02016 0.01347 0.0046 0.0323 1.0000
9.750 1.0502 0.02069 0.01401 0.0056 0.0313 1.0000
10.000 1.0667 0.02159 0.01491 0.0070 0.0303 1.0000
10.250 1.0849 0.02233 0.01574 0.0082 0.0294 1.0000
10.500 1.1035 0.02294 0.01645 0.0094 0.0284 1.0000
10.750 1.1214 0.02357 0.01714 0.0106 0.0275 1.0000
11.000 1.1384 0.02420 0.01780 0.0119 0.0267 1.0000
11.250 1.1518 0.02498 0.01859 0.0136 0.0261 1.0000
11.500 1.1611 0.02629 0.01995 0.0158 0.0254 1.0000
11.750 1.1730 0.02724 0.02103 0.0176 0.0248 1.0000
12.000 1.1840 0.02832 0.02223 0.0193 0.0242 1.0000
12.250 1.1942 0.02949 0.02350 0.0209 0.0237 1.0000
12.500 1.2040 0.03070 0.02480 0.0223 0.0232 1.0000
12.750 1.2131 0.03197 0.02615 0.0236 0.0229 1.0000
13.000 1.2216 0.03336 0.02760 0.0247 0.0225 1.0000
13.250 1.2290 0.03493 0.02923 0.0257 0.0223 1.0000
13.500 1.2345 0.03681 0.03119 0.0266 0.0220 1.0000
13.750 1.2361 0.03935 0.03384 0.0276 0.0217 1.0000
14.000 1.2365 0.04194 0.03660 0.0282 0.0215 1.0000
14.250 1.2362 0.04461 0.03945 0.0284 0.0214 1.0000
14.500 1.2336 0.04766 0.04268 0.0283 0.0213 1.0000
14.750 1.2288 0.05112 0.04632 0.0278 0.0212 1.0000
15.000 1.2211 0.05507 0.05047 0.0268 0.0211 1.0000
15.250 1.2106 0.05956 0.05515 0.0254 0.0210 1.0000
15.500 1.1970 0.06465 0.06044 0.0234 0.0210 1.0000
15.750 1.1799 0.07048 0.06648 0.0208 0.0209 1.0000
16.000 1.1593 0.07713 0.07333 0.0174 0.0210 1.0000
16.250 1.1353 0.08475 0.08115 0.0133 0.0210 1.0000
16.500 1.1073 0.09353 0.09014 0.0082 0.0211 1.0000
16.750 1.0742 0.10383 0.10065 0.0021 0.0212 1.0000
17.000 1.0331 0.11662 0.11365 -0.0058 0.0213 1.0000
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